Airworthiness Directives; The Boeing Company Airplanes, 22928-22932 [2024-06993]
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22928
Federal Register / Vol. 89, No. 65 / Wednesday, April 3, 2024 / Rules and Regulations
FAA–2023–1046; Project Identifier AD–
2023–00253–T.
(a) Effective Date
This airworthiness directive (AD) is
effective May 8, 2024.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 757–200, –200CB, and –300 series
airplanes, certificated in any category, as
identified in Boeing Alert Requirements
Bulletin 757–53A0121 RB, dated September
28, 2022.
(d) Subject
Air Transport Association (ATA) of
America Code: 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report of a
crack at fuselage station (STA) 1640 frame
web common to the lower hinge intercostal
tee clip center hole of the upper fastener row.
This condition, if not addressed, could result
in the inability of a principal structural
element to sustain limit loads, which could
adversely affect the structural integrity 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 the
‘‘Compliance’’ paragraph of Boeing Alert
Requirements Bulletin 757–53A0121 RB,
dated September 28, 2022, do all applicable
actions identified in, and in accordance with,
the Accomplishment Instructions of Boeing
Alert Requirements Bulletin 757–53A0121
RB, dated September 28, 2022.
Note 1 to paragraph (g): Guidance for
accomplishing the actions required by this
AD can be found in Boeing Alert Service
Bulletin 757–53A0121, dated September 28,
2022, which is referred to in Boeing Alert
Requirements Bulletin 757–53A0121 RB,
dated September 28, 2022.
(h) Exceptions to Service Information
Specifications
(1) Where the Compliance Time columns
of the tables in the ‘‘Compliance’’ paragraph
of Boeing Alert Requirements Bulletin 757–
53A0121 RB, dated September 28, 2022, use
the phrase ‘‘the original issue date of
Requirements Bulletin 757–53A0121 RB,’’
this AD requires replacing those words with
‘‘the effective date of this AD.’’
(2) Where Boeing Alert Requirements
Bulletin 757–53A0121 RB, dated September
28, 2022, 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 using a
method approved in accordance with the
procedures specified in paragraph (i) of this
AD.
(3) For airplanes modified in accordance
with Aviation Partners Boeing (APB)
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Supplemental Type Certificate (STC)
ST01518SE, with or without blended or
scimitar blended winglets installed: This AD
requires dividing the applicable compliance
times and repeat intervals specified in the
‘‘Compliance’’ paragraph of Boeing Alert
Requirements Bulletin 757–53A0121 RB,
dated September 28, 2022, by a factor of two.
(4) For Group 1 airplanes identified in
Boeing Alert Requirements Bulletin 757–
53A0121 RB, dated September 28, 2022, that
have been converted from passenger to
freighter configuration using VT MAE STC
ST03562AT or ST03952AT and that have a
long inner chord strap part number
146N8711–65 at the STA 1640 fuselage
frame: The actions specified in paragraph (g)
of this AD are not required.
(5) For Group 3 airplanes identified in
Boeing Alert Requirements Bulletin 757–
53A0121 RB, dated September 28, 2022, that
have been converted from passenger to
freighter configuration using VT MAE STC
ST03562AT: Do all applicable actions for
Group 4, as identified in, and in accordance
with, Boeing Alert Requirements Bulletin
757–53A0121 RB, dated September 28, 2022,
at the applicable times for Group 4 as
specified in the ‘‘Compliance’’ paragraph of
Boeing Alert Requirements Bulletin 757–
53A0121 RB, dated September 28, 2022.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Boeing Alert Requirements Bulletin
757–53A0121 RB, dated September 28, 2022.
(ii) [Reserved]
(3) For material identified in this AD,
contact Boeing Commercial Airplanes,
Attention: Contractual & Data Services
(C&DS), 2600 Westminster Boulevard, MC
110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; website:
myboeingfleet.com.
(4) You may view this material that is
incorporated by reference at the FAA,
Airworthiness Products Section, Operational
Safety Branch, 2200 South 216th Street, Des
Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195.
(5) You may view this material at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
visit www.archives.gov/federal-register/cfr/
ibr-locations or emailfr.inspection@nara.gov.
(i) Alternative Methods of Compliance
(AMOCs)
Issued on March 4, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
(1) The Manager, Continued Operational
Safety 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: 9-ANMSACO-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, Continued Operational Safety
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 Wayne Ha, Aviation Safety Engineer,
Continued Operational Safety Branch, FAA,
2200 South 216th Street, Des Moines, WA
98198; phone: 562–627–5238; email:
wayne.ha@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the address specified in
paragraph (k)(3) of this AD.
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[FR Doc. 2024–06995 Filed 4–2–24; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2023–1986; Project
Identifier AD–2022–00015–T; Amendment
39–22693; AD 2024–05–03]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 767
airplanes. This AD was prompted by a
report of cracks on the forward entry
door and forward service door cutout aft
lower corner fuselage skin and bear
strap. This AD requires repetitive
inspections for cracking at the affected
area, and applicable on-condition
actions. The FAA is issuing this AD to
address the unsafe condition on these
products.
DATES: This AD is effective May 8, 2024.
SUMMARY:
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Federal Register / Vol. 89, No. 65 / Wednesday, April 3, 2024 / Rules and Regulations
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 8, 2024.
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2023–1986; 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 final rule, any comments
received, and other information. The
address for Docket Operations is U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE, Washington, DC
20590.
Material Incorporated by Reference:
• For service information identified
in this final rule, 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; website
myboeingfleet.com.
• You may view service information
that is incorporated by reference 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 regulations.gov
under Docket No. FAA–2022–1986.
FOR FURTHER INFORMATION CONTACT:
Joseph Hodgin, Aviation Safety
Engineer, FAA, 2200 South 216th St.,
Des Moines, WA 98198; phone: 206–
231–3962; email: Joseph.J.Hodgin@
faa.gov.
SUPPLEMENTARY INFORMATION:
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Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model 767 airplanes. The NPRM
published in the Federal Register on
October 5, 2023 (88 FR 69107). The
NPRM was prompted by a report of
cracks on the forward entry door and
forward service door cutout aft lower
corner fuselage skin and bear strap. In
the NPRM, the FAA proposed to require
repetitive inspections for cracking at the
affected area, and applicable oncondition actions. The FAA is issuing
this AD to address undetected fatigue
cracks which, if not addressed, could
result in a principal structural element’s
loss of limit load capability, adversely
affecting the airplane’s structural
integrity.
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22929
Discussion of Final Airworthiness
Directive
Request for Repetitive Inspections To
Be Outlined if No Crack Is Found
Comments
Boeing requested that the AD include
repetitive inspections for Model 767–2C
if no crack is found. This change is
requested to maintain the safety of the
fleet since paragraph (i) of this AD
should include all follow-on actions for
the condition of no crack found.
The FAA agrees with adding the
repetitive inspections to account for all
follow-on actions for no crack found to
maintain the safety of the fleet.
Paragraph (i) of this AD is revised to
include the repetitive inspections.
Boeing also requested that paragraph
(j) of this AD be changed to reference
the Airworthiness Limitations (AWL)
document associated with the
Compliance Time Definitions for Model
767–2C airplanes. The commenter is
concerned with the redefining
compliance times already defined
within the AWL, which could create a
conflict with the rule that would require
a rule revision if the definitions in the
AWL were to be redefined.
The FAA disagrees. The FAA’s intent
is for the compliance time terms used in
paragraph (j) of this AD to be the same
terms already defined in the Model 767–
2C Airworthiness Limitations
document. Including the compliance
time definitions for Model 767–2C in
paragraph (j) of this AD ensures that
those definitions are followed,
notwithstanding any future changes to
the definitions in the AWL. If the
compliance time definitions in the AWL
are changed in the future, the FAA will
consider revising this Airworthiness
Directive at that time. In any event, an
operator may request approval to use
later revised compliance time
definitions as an alternative method of
compliance (under the provisions of
paragraph (l) of this AD).
The FAA received comments from
three commenters who supported the
NPRM without change.
The FAA received additional
comments from five commenters,
including ABX Air, All Nippon
Airways, Boeing, United Airlines, and
UPS. The following presents the
comments received on the NPRM and
the FAA’s response to each comment.
Request for Clarification of Exemption
From Alternative Methods of
Compliance (AMOC)
ABX Air requested clarification as to
whether repairs performed using
approval via Form 8110–3 are exempt
from needing an AMOC for this AD,
similar to repairs made using approval
via Form 8100–9 repairs. The
commenter provided no justification for
the request.
Repairs performed using Form 8110–
3 are not exempt from requiring an
AMOC for this AD. As specified in
paragraph (l)(3) of this AD, only those
repairs, modifications, or alterations
required by this AD are exempt from an
FAA approved-AMOC if those AMOCs
are approved by The Boeing Company
Organization Designation Authorization
(ODA) that has been authorized by the
Manager, AIR–520, Continued
Operational Safety Branch, FAA, to
make those findings. All other repairs,
including those approved on Form
8110–3, will require an AMOC
approved in accordance with paragraph
(l) of this AD. This is necessary to
ensure the repairs maintain an adequate
level of safety.
Request for Inclusion of B767–300BCF
SRM as an Acceptable Method of
Compliance
All Nippon Airways requested that
the proposed rule be modified to
include B767–300BCF SRM Repair 1 as
an acceptable method of compliance. It
was not listed as a method of
compliance whereas 767–200, –300,
–300F, and –400 SRMs were in Tables
1 and 2(a). The commenter requested
this change because All Nippon
Airways owns 767–300BCF aircraft.
The FAA agrees with this change
because the repairs and repeat
instructions are the same for B767–
300BCF as the B767–300 SRM. The FAA
has revised paragraph (h) of this AD to
include exceptions for repairs
performed in accordance with B767–
300BCF SRM 53–10–01 Repair 1.
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Request for Change To State That a Ref/
C/SRM Repair Terminates the Need for
Repetitive Inspections
United Airlines requested the AD be
amended to state that repetitive
inspections associated with Boeing
Alert Requirements Bulletin 767–
53A0301 RB, Revision 2, dated May 24,
2023 conditions 3, 4, 7, and 8 (Ref/B)
are not required in areas covered by 53–
10–01 Repair 1 of the applicable Model
767 SRM (Ref/C/SRM) if done after the
initial inspections required by Ref/B/
RB. This change is requested because
the commenter believes that the
installation of a Ref/C/SRM repair after
the initial Ref/B/RB inspection should
provide at least an equivalent level of
safety with the unsafe condition this AD
is addressing. The FAA disagrees with
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Federal Register / Vol. 89, No. 65 / Wednesday, April 3, 2024 / Rules and Regulations
revising the AD to state that a Ref/C/
SRM repair terminates the need for
repetitive inspections associated with
RB conditions 3, 4, 7, and 8. In the RB
Section 5 Accomplishment Instruction
Tables 1 and 2, there is note (c) which
states that accomplishment of 53–10–01
Repair 1 of the applicable Model 767
SRM is terminating action for the
inspections at this location only. The
FAA has determined that note (c)
sufficiently outlines that performing
repair 1 is the terminating action for the
inspections at that location and no
further clarification is necessary.
of ‘‘Compliance Time Definitions’’ to
avoid confusion.
The FAA disagrees with changing
paragraph (g) of this AD language
because paragraph (c) of this AD
specifies the applicability of the AD and
therefore the airplane models affected
by paragraph (g) of this AD. For
clarification, airplanes not identified in
paragraph (c) of this AD are not affected
by any paragraph of this AD. The FAA
agrees with revising paragraph (j) of this
AD to state ‘‘Compliance Time
Definitions for Model 767–2C’’ for
clarity.
Request Change to Paragraphs (g) and
(j) of This AD for Clarity
Conclusion
The FAA reviewed the relevant data,
considered any comments received, and
determined that air safety requires
adopting this AD as proposed.
Accordingly, the FAA is issuing this AD
to address the unsafe condition on these
products. Except for minor editorial
changes, and any other changes
described previously, this AD is
adopted as proposed in the NPRM.
None of the changes will increase the
economic burden on any operator.
UPS requested amending paragraph
(g) of this AD to state ‘‘For Model 767–
200, –300, –300F, or –400ER series
airplanes, as identified in Section (c)
Applicability of the AD’’ to avoid
confusion on where applicability is
established in the AD.
UPS also requested revising paragraph
(j) of this AD to state ‘‘Compliance Time
Definitions for Model 767–2C’’ instead
Related Service Information Under 1
CFR Part 51
The FAA reviewed Boeing Alert
Requirements Bulletin 767–3A0301 RB,
Revision 2, dated May 24, 2023. This
service information specifies procedures
for repetitive inspections (external
detailed, internal detailed, and open
hole high frequency eddy current) for
cracking at the forward entry door and
forward service door cutout aft lower
corner fuselage skin and bear strap area.
This service information also specifies
procedures for on-condition actions,
including crack 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 ADDRESSES.
Costs of Compliance
The FAA estimates that this AD
affects 682 airplanes of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Inspections .............................
Up to 8 work-hours × $85 per
hour = Up to $680 per inspection cycle.
The FAA has received no definitive
data on which to base the cost estimates
for the on-condition actions (i.e.,
possible crack repair) specified in this
AD.
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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.
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Parts cost
Cost per product
$0
Up to $680 per inspection
cycle.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will 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 this AD:
(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 Amendment
Accordingly, under the authority
delegated to me by the Administrator,
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Cost on U.S. operators
Up to $463,760 per inspection
cycle.
the FAA amends 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:
■
2024–05–03 The Boeing Company:
Amendment 39–22693; Docket No.
FAA–2023–1986; Project Identifier AD–
2022–00015–T.
(a) Effective Date
This airworthiness directive (AD) is
effective May 8, 2024.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
airplanes, certificated in any category,
identified in paragraphs (c)(1) and (2) of this
AD.
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Federal Register / Vol. 89, No. 65 / Wednesday, April 3, 2024 / Rules and Regulations
(1) Model 767–200, –300, –300F, and
–400ER series airplanes, as identified in
Boeing Alert Requirements Bulletin 767–
53A0301 RB, Revision 2, dated May 24, 2023.
(2) Model 767–2C series airplanes, line
numbers 1065, 1066, 1067, 1069, 1091, 1092,
1098, 1100, 1102, 1104, 1107, 1109, 1111,
1113, 1114, 1116, 1117, 1119, 1120, 1122,
1124, 1126, 1128, 1129, 1131, 1132, 1134,
1135, 1137, 1139, 1143, 1145, 1147, 1149,
1151, 1154, 1156, 1158, 1160, 1162, 1164,
1166, 1168, 1170, 1172, 1174, 1176, 1178,
1181, 1184, 1188, 1192, 1196, 1200, 1202,
1205, 1207, 1210, 1213, 1216, 1219, 1223,
1226, 1230, 1234, 1236, 1238, 1241, 1243,
1246, 1248, 1250, 1252, 1254, 1257, 1259,
1261, 1264, 1267, 1269, 1271, and 1273.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report of
cracks found on the forward entry door and
forward service door cutout aft lower corner
fuselage skin and bear strap. The FAA is
issuing this AD to address undetected fatigue
cracks. The unsafe condition, if not
addressed, could result in a principal
structural element losing its limit load
capability, adversely affecting the airplane’s
structural integrity.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Required Actions: Model 767–200, –300,
–300F, and –400ER
For Model 767–200, –300, –300F, –400ER
series airplanes: Except as specified by
paragraph (h) of this AD, at the applicable
times specified in the ‘‘Compliance’’
paragraph of Boeing Alert Requirements
Bulletin 767–53A0301 RB, Revision 2, dated
May 24, 2023, do all applicable actions
identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert
Requirements Bulletin 767–53A0301 RB,
Revision 2, dated May 24, 2023.
Note 1 to paragraph (g): Guidance for
accomplishing the actions required by this
AD can be found in Boeing Alert Service
Bulletin 767–53A0301, Revision 2, dated
May 24, 2023, which is referred to in Boeing
Alert Requirements Bulletin 767–53A0301,
Revision 2, dated May 24, 2023.
(h) Exceptions to Service Information
Specifications
(1) Where Boeing Alert Requirements
Bulletin 767–53A0301 RB, dated May 24,
2023, compliance time columns in Tables 1
and 2, paragraph E (Compliance), use the
phrase ‘‘the Original Issue date of
Requirements Bulletin 767–53A0301 RB,’’
this AD requires using the effective date of
this AD.
(2) Where Boeing Alert Requirements
Bulletin 767–53A0301 RB, Revision 2, dated
May 24, 2023, specifies contacting Boeing for
repair instructions: This AD requires doing
the repair before further flight using a
method approved in accordance with the
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procedures specified in paragraph (l) of this
AD.
(3) Where Boeing Alert Requirements
Bulletin 767–53A0301 RB, Revision 2, dated
May 24, 2023, refers to ‘‘767–200 SRM 53–
10–01 Repair 1, 767–300 SRM 53–10–01
Repair 1, 767–300F SRM 53–10–01 Repair 1
or 767–400 SRM 53–10–01 Repair 1,’’ this
AD requires replacing that text with ‘‘767–
200 SRM 53–10–01 Repair 1, 767–300 SRM
53–10–01 Repair 1, 767–300F SRM 53–10–01
Repair 1, 767–400 SRM 53–10–01 Repair 1,
or B767–300BCF SRM 53–10–01 Repair 1, as
applicable.’’
(4) Where Boeing Alert Requirements
Bulletin 767–53A0301 RB, Revision 2, dated
May 24, 2023, refers to ‘‘767–200 SRM 53–
10–01 Repair 1, 767–300 SRM 53–10–01
Repair 1, or 767–400 SRM 53–10–01 Repair
1,’’ this AD requires replacing that text with
‘‘767–200 SRM 53–10–01 Repair 1, 767–300
SRM 53–10–01 Repair 1, 767–400 SRM 53–
10–01 Repair 1, or B767–300BCF SRM 53–
10–01 Repair 1, as applicable.’’
(i) Required Actions: Model 767–2C
At the later of the times specified in
paragraphs (i)(1) and (2) of this AD: Perform
inspections (external detailed, internal
detailed, and open hole high frequency eddy
current, as applicable), including repetitive
inspections as applicable, for cracking at the
forward entry door and forward service door
cutout aft lower corner fuselage skin and bear
strap area, and repair any cracks found, in
accordance with a method and at the times
specified, as approved by the Manager, AIR–
520, Continued Operational Safety Branch,
FAA.
Note 2 to paragraph (i): Guidance on doing
the required actions can be found in Boeing
Alert Requirements Bulletin 767–53A0303
RB, Revision 1, dated June 29, 2023; and
Boeing Alert Requirements Bulletin 767–
53A0308, Revision 1, dated June 21, 2023.
(1) Before 15,000 cumulative flight cycles
or 30,000 cumulative total accumulated
cycles, whichever occurs first. These terms
are defined in paragraph (j) of this AD.
(2) Within 2,250 flight cycles, 4,500 total
accumulated cycles, or 24 months after the
effective date of this AD, whichever occurs
first.
(j) Compliance Time Definitions for Model
767–2C
The definitions in paragraphs (j)(1) through
(5) of this AD apply to this AD.
(1) A ‘‘flight cycle’’ is an operation by an
aircraft that is initially stopped on the
ground, departs in flight, attains a maximum
above ground level (AGL) altitude greater
than 5,000 feet relative to the runway, lands
on a runway, and stops on the ground. A
flight cycle may include one or more touchand-go cycles.
(2) A ‘‘touch-and-go cycle’’ is an operation
by an aircraft that lands and departs on a
runway without stopping or exiting the
runway and is immediately followed by a
short flight with a maximum AGL altitude of
5,000 feet relative to the runway.
(3) ‘‘Total accumulated cycles’’ is the sum
of the accumulated number of flight cycles,
accumulated missed approaches, and the
accumulated number of touch-and-go cycles.
PO 00000
Frm 00029
Fmt 4700
Sfmt 4700
22931
(4) A ‘‘missed approach’’ (or go-around) is
an aircraft landing approach that is
discontinued and proceeded by a climb-out
for any reason without landing gear touching
the runway and is either immediately
preceded by or immediately followed by a
short flight with a maximum AGL altitude of
5,000 feet relative to the runway. Any flight
operation not meeting this definition is
considered a flight cycle.
(5) ‘‘Cumulative’’ cycles are total cycles
since new.
(k) Credit for Previous Actions
This paragraph provides credit for the
actions specified in paragraph (g) of this AD,
if those actions were performed before the
effective date of this AD using Boeing Alert
Requirements Bulletin 767–53A0301 RB,
dated April 21, 2021, or Boeing Alert
Requirements Bulletin 767–53A0301 RB,
Revision 1, dated April 11, 2022.
(l) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, AIR–520, Continued
Operational Safety 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 (m)(1) of this AD.
Information may be emailed to: 9-ANMSeattle-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, AIR–520, Continued Operational
Safety 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.
(m) Related Information
(1) For more information about this AD,
contact Joseph Hodgin, Aviation Safety
Engineer, FAA, 2200 South 216th St., Des
Moines, WA 98198; phone: 206–231–3962;
email: Joseph.J.Hodgin@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the address specified in
paragraph (n)(3) of this AD.
(n) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
E:\FR\FM\03APR1.SGM
03APR1
22932
Federal Register / Vol. 89, No. 65 / Wednesday, April 3, 2024 / Rules and Regulations
(i) Boeing Alert Requirements Bulletin
767–53A0301 RB, Revision 2, dated May 24,
2023.
(ii) [Reserved]
(3) 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; website
myboeingfleet.com.
(4) You may view service information that
is incorporated by reference 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.
(5) You may view this material at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
visit www.archives.gov/federal-register/cfr/
ibr-locations or email fr.inspection@nara.gov.
Issued on February 29, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2024–06993 Filed 4–2–24; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2023–1897; Project
Identifier MCAI–2023–00921–T; Amendment
39–22692; AD 2024–05–02]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus SAS Model A320–214, A320–
216, A320–251N, A320–271N, and
A321–253NX airplanes. This AD was
prompted by a quality review of the
forward cargo door frame-to-fuselage
skin panel assembly identified several
fastener holes that deviated from the
manufacturing requirements. This AD
requires a geometrical check of the
diameter of certain fastener holes for
deviations, and if any deviation is
found, repetitive special detailed
inspections of the affected area for
discrepancies and, depending on
findings, accomplishment of applicable
corrective actions, as specified in a
European Union Aviation Safety Agency
(EASA) AD, which is incorporated by
reference. The FAA is issuing this AD
lotter on DSK11XQN23PROD with RULES1
SUMMARY:
VerDate Sep<11>2014
17:20 Apr 02, 2024
Jkt 262001
to address the unsafe condition on these
products.
DATES: This AD is effective May 8, 2024.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 8, 2024.
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2023–1897; 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 final rule, the mandatory
continuing airworthiness information
(MCAI), any comments received, and
other information. The address for
Docket Operations is U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
Material Incorporated by Reference:
• For material identified in this AD,
contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49
221 8999 000; email ADs@
easa.europa.eu; website easa.europa.eu.
You may find this material on the EASA
website ad.easa.europa.eu.
• You may view this material at the
FAA, Airworthiness Products Section,
Operational Safety Branch, 2200 South
216th Street, Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available in the AD docket at
regulations.gov under Docket No. FAA–
2023–1897.
FOR FURTHER INFORMATION CONTACT:
Timothy Dowling, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590;
telephone: 206–231–3667; email:
timothy.p.dowling@faa.gov.
SUPPLEMENTARY INFORMATION:
oversized fastener holes, which could
lead to cracking. This condition, if not
addressed, could lead to reduced
structural integrity of the fuselage.
In the NPRM, the FAA proposed to
require repetitive special detailed
inspections of the affected area for
discrepancies and, depending on
findings, accomplishment of applicable
corrective actions, as specified in EASA
AD 2023–0153. The FAA is issuing this
AD to address the unsafe condition on
these products.
You may examine the MCAI in the
AD docket at regulations.gov under
Docket No. FAA–2023–1897.
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Airbus SAS Model
A320–214, A320–216, A320–251N,
A320–271N, and A321–253NX
airplanes. The NPRM published in the
Federal Register on October 5, 2023 (88
FR 69110). The NPRM was prompted by
AD 2023–0153, dated July 26, 2023
(EASA AD 2023–0153) (also referred to
as the MCAI), issued by EASA, which
is the Technical Agent for the Member
States of the European Union. The
MCAI states a quality review of the
forward cargo door frame-to-fuselage
skin panel assembly identified several
drillings as deviating from
manufacturing requirements, creating
Conclusion
This product has been approved by
the aviation authority of another
country and is approved for operation in
the United States. Pursuant to the FAA’s
bilateral agreement with this State of
Design Authority, it has notified the
FAA of the unsafe condition described
in the MCAI referenced above. The FAA
reviewed the relevant data, considered
the comments received, and determined
that air safety requires adopting this AD
as proposed. Accordingly, the FAA is
issuing this AD to address the unsafe
condition on this product. Except for
minor editorial changes, and any other
changes described previously, this AD is
adopted as proposed in the NPRM.
None of the changes will increase the
economic burden on any operator.
PO 00000
Frm 00030
Fmt 4700
Sfmt 4700
Discussion of Final Airworthiness
Directive
Comments
The FAA received comments from
two commenters. Air Line Pilots
Association, International (ALPA) and
an individual who both supported the
NPRM without change.
Additional Changes Made to This AD
Since the NPRM was published,
EASA AD 2023–0153 was superseded
by EASA AD 2023–0179, dated October
11, 2023 (EASA AD 2023–0179). Since
EASA AD 2023–0153 was issued, it has
been determined that, depending on
inspection findings, no repetitive
inspection may be required. EASA AD
2023–0179 also clarified that the initial
inspection is a geometrical check of the
diameter of certain fastener holes for
deviations. The FAA has updated this
final rule accordingly by replacing
EASA AD 2023–0153 with EASA AD
2023–0179 in all affected paragraphs
and added a ‘‘Credit for Previous
Actions’’ paragraph to retain the
requirements of EASA AD 2023–0153,
however the concession identified in
EASA AD 2023–0153 was removed in
EASA AD 2023–0179.
E:\FR\FM\03APR1.SGM
03APR1
]]>Agencies
[Federal Register Volume 89, Number 65 (Wednesday, April 3, 2024)]
[Rules and Regulations]
[Pages 22928-22932]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-06993]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2023-1986; Project Identifier AD-2022-00015-T;
Amendment 39-22693; AD 2024-05-03]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain The Boeing Company Model 767 airplanes. This AD was prompted by
a report of cracks on the forward entry door and forward service door
cutout aft lower corner fuselage skin and bear strap. This AD requires
repetitive inspections for cracking at the affected area, and
applicable on-condition actions. The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective May 8, 2024.
[[Page 22929]]
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 8, 2024.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2023-1986; 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 final rule, any comments received, and other
information. The address for Docket Operations is U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
Material Incorporated by Reference:
For service information identified in this final rule,
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; website myboeingfleet.com.
You may view service information that is incorporated by
reference 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 regulations.gov under Docket No. FAA-2022-1986.
FOR FURTHER INFORMATION CONTACT: Joseph Hodgin, Aviation Safety
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-
231-3962; email: [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain The Boeing
Company Model 767 airplanes. The NPRM published in the Federal Register
on October 5, 2023 (88 FR 69107). The NPRM was prompted by a report of
cracks on the forward entry door and forward service door cutout aft
lower corner fuselage skin and bear strap. In the NPRM, the FAA
proposed to require repetitive inspections for cracking at the affected
area, and applicable on-condition actions. The FAA is issuing this AD
to address undetected fatigue cracks which, if not addressed, could
result in a principal structural element's loss of limit load
capability, adversely affecting the airplane's structural integrity.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from three commenters who supported the
NPRM without change.
The FAA received additional comments from five commenters,
including ABX Air, All Nippon Airways, Boeing, United Airlines, and
UPS. The following presents the comments received on the NPRM and the
FAA's response to each comment.
Request for Clarification of Exemption From Alternative Methods of
Compliance (AMOC)
ABX Air requested clarification as to whether repairs performed
using approval via Form 8110-3 are exempt from needing an AMOC for this
AD, similar to repairs made using approval via Form 8100-9 repairs. The
commenter provided no justification for the request.
Repairs performed using Form 8110-3 are not exempt from requiring
an AMOC for this AD. As specified in paragraph (l)(3) of this AD, only
those repairs, modifications, or alterations required by this AD are
exempt from an FAA approved-AMOC if those AMOCs are approved by The
Boeing Company Organization Designation Authorization (ODA) that has
been authorized by the Manager, AIR-520, Continued Operational Safety
Branch, FAA, to make those findings. All other repairs, including those
approved on Form 8110-3, will require an AMOC approved in accordance
with paragraph (l) of this AD. This is necessary to ensure the repairs
maintain an adequate level of safety.
Request for Inclusion of B767-300BCF SRM as an Acceptable Method of
Compliance
All Nippon Airways requested that the proposed rule be modified to
include B767-300BCF SRM Repair 1 as an acceptable method of compliance.
It was not listed as a method of compliance whereas 767-200, -300, -
300F, and -400 SRMs were in Tables 1 and 2(a). The commenter requested
this change because All Nippon Airways owns 767-300BCF aircraft.
The FAA agrees with this change because the repairs and repeat
instructions are the same for B767-300BCF as the B767-300 SRM. The FAA
has revised paragraph (h) of this AD to include exceptions for repairs
performed in accordance with B767-300BCF SRM 53-10-01 Repair 1.
Request for Repetitive Inspections To Be Outlined if No Crack Is Found
Boeing requested that the AD include repetitive inspections for
Model 767-2C if no crack is found. This change is requested to maintain
the safety of the fleet since paragraph (i) of this AD should include
all follow-on actions for the condition of no crack found.
The FAA agrees with adding the repetitive inspections to account
for all follow-on actions for no crack found to maintain the safety of
the fleet. Paragraph (i) of this AD is revised to include the
repetitive inspections.
Boeing also requested that paragraph (j) of this AD be changed to
reference the Airworthiness Limitations (AWL) document associated with
the Compliance Time Definitions for Model 767-2C airplanes. The
commenter is concerned with the redefining compliance times already
defined within the AWL, which could create a conflict with the rule
that would require a rule revision if the definitions in the AWL were
to be redefined.
The FAA disagrees. The FAA's intent is for the compliance time
terms used in paragraph (j) of this AD to be the same terms already
defined in the Model 767-2C Airworthiness Limitations document.
Including the compliance time definitions for Model 767-2C in paragraph
(j) of this AD ensures that those definitions are followed,
notwithstanding any future changes to the definitions in the AWL. If
the compliance time definitions in the AWL are changed in the future,
the FAA will consider revising this Airworthiness Directive at that
time. In any event, an operator may request approval to use later
revised compliance time definitions as an alternative method of
compliance (under the provisions of paragraph (l) of this AD).
Request for Change To State That a Ref/C/SRM Repair Terminates the Need
for Repetitive Inspections
United Airlines requested the AD be amended to state that
repetitive inspections associated with Boeing Alert Requirements
Bulletin 767-53A0301 RB, Revision 2, dated May 24, 2023 conditions 3,
4, 7, and 8 (Ref/B) are not required in areas covered by 53-10-01
Repair 1 of the applicable Model 767 SRM (Ref/C/SRM) if done after the
initial inspections required by Ref/B/RB. This change is requested
because the commenter believes that the installation of a Ref/C/SRM
repair after the initial Ref/B/RB inspection should provide at least an
equivalent level of safety with the unsafe condition this AD is
addressing. The FAA disagrees with
[[Page 22930]]
revising the AD to state that a Ref/C/SRM repair terminates the need
for repetitive inspections associated with RB conditions 3, 4, 7, and
8. In the RB Section 5 Accomplishment Instruction Tables 1 and 2, there
is note (c) which states that accomplishment of 53-10-01 Repair 1 of
the applicable Model 767 SRM is terminating action for the inspections
at this location only. The FAA has determined that note (c)
sufficiently outlines that performing repair 1 is the terminating
action for the inspections at that location and no further
clarification is necessary.
Request Change to Paragraphs (g) and (j) of This AD for Clarity
UPS requested amending paragraph (g) of this AD to state ``For
Model 767-200, -300, -300F, or -400ER series airplanes, as identified
in Section (c) Applicability of the AD'' to avoid confusion on where
applicability is established in the AD.
UPS also requested revising paragraph (j) of this AD to state
``Compliance Time Definitions for Model 767-2C'' instead of
``Compliance Time Definitions'' to avoid confusion.
The FAA disagrees with changing paragraph (g) of this AD language
because paragraph (c) of this AD specifies the applicability of the AD
and therefore the airplane models affected by paragraph (g) of this AD.
For clarification, airplanes not identified in paragraph (c) of this AD
are not affected by any paragraph of this AD. The FAA agrees with
revising paragraph (j) of this AD to state ``Compliance Time
Definitions for Model 767-2C'' for clarity.
Conclusion
The FAA reviewed the relevant data, considered any comments
received, and determined that air safety requires adopting this AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products. Except for minor editorial changes, and
any other changes described previously, this AD is adopted as proposed
in the NPRM. None of the changes will increase the economic burden on
any operator.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Boeing Alert Requirements Bulletin 767-3A0301 RB,
Revision 2, dated May 24, 2023. This service information specifies
procedures for repetitive inspections (external detailed, internal
detailed, and open hole high frequency eddy current) for cracking at
the forward entry door and forward service door cutout aft lower corner
fuselage skin and bear strap area. This service information also
specifies procedures for on-condition actions, including crack 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 ADDRESSES.
Costs of Compliance
The FAA estimates that this AD affects 682 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspections...................... Up to 8 work-hours $0 Up to $680 per Up to $463,760 per
x $85 per hour = inspection cycle. inspection cycle.
Up to $680 per
inspection cycle.
----------------------------------------------------------------------------------------------------------------
The FAA has received no definitive data on which to base the cost
estimates for the on-condition actions (i.e., possible crack repair)
specified in this 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.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will 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 this AD:
(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 Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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:
2024-05-03 The Boeing Company: Amendment 39-22693; Docket No. FAA-
2023-1986; Project Identifier AD-2022-00015-T.
(a) Effective Date
This airworthiness directive (AD) is effective May 8, 2024.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company airplanes, certificated in
any category, identified in paragraphs (c)(1) and (2) of this AD.
[[Page 22931]]
(1) Model 767-200, -300, -300F, and -400ER series airplanes, as
identified in Boeing Alert Requirements Bulletin 767-53A0301 RB,
Revision 2, dated May 24, 2023.
(2) Model 767-2C series airplanes, line numbers 1065, 1066,
1067, 1069, 1091, 1092, 1098, 1100, 1102, 1104, 1107, 1109, 1111,
1113, 1114, 1116, 1117, 1119, 1120, 1122, 1124, 1126, 1128, 1129,
1131, 1132, 1134, 1135, 1137, 1139, 1143, 1145, 1147, 1149, 1151,
1154, 1156, 1158, 1160, 1162, 1164, 1166, 1168, 1170, 1172, 1174,
1176, 1178, 1181, 1184, 1188, 1192, 1196, 1200, 1202, 1205, 1207,
1210, 1213, 1216, 1219, 1223, 1226, 1230, 1234, 1236, 1238, 1241,
1243, 1246, 1248, 1250, 1252, 1254, 1257, 1259, 1261, 1264, 1267,
1269, 1271, and 1273.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report of cracks found on the forward
entry door and forward service door cutout aft lower corner fuselage
skin and bear strap. The FAA is issuing this AD to address
undetected fatigue cracks. The unsafe condition, if not addressed,
could result in a principal structural element losing its limit load
capability, adversely affecting the airplane's structural integrity.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions: Model 767-200, -300, -300F, and -400ER
For Model 767-200, -300, -300F, -400ER series airplanes: Except
as specified by paragraph (h) of this AD, at the applicable times
specified in the ``Compliance'' paragraph of Boeing Alert
Requirements Bulletin 767-53A0301 RB, Revision 2, dated May 24,
2023, do all applicable actions identified in, and in accordance
with, the Accomplishment Instructions of Boeing Alert Requirements
Bulletin 767-53A0301 RB, Revision 2, dated May 24, 2023.
Note 1 to paragraph (g): Guidance for accomplishing the actions
required by this AD can be found in Boeing Alert Service Bulletin
767-53A0301, Revision 2, dated May 24, 2023, which is referred to in
Boeing Alert Requirements Bulletin 767-53A0301, Revision 2, dated
May 24, 2023.
(h) Exceptions to Service Information Specifications
(1) Where Boeing Alert Requirements Bulletin 767-53A0301 RB,
dated May 24, 2023, compliance time columns in Tables 1 and 2,
paragraph E (Compliance), use the phrase ``the Original Issue date
of Requirements Bulletin 767-53A0301 RB,'' this AD requires using
the effective date of this AD.
(2) Where Boeing Alert Requirements Bulletin 767-53A0301 RB,
Revision 2, dated May 24, 2023, specifies contacting Boeing for
repair instructions: This AD requires doing the repair before
further flight using a method approved in accordance with the
procedures specified in paragraph (l) of this AD.
(3) Where Boeing Alert Requirements Bulletin 767-53A0301 RB,
Revision 2, dated May 24, 2023, refers to ``767-200 SRM 53-10-01
Repair 1, 767-300 SRM 53-10-01 Repair 1, 767-300F SRM 53-10-01
Repair 1 or 767-400 SRM 53-10-01 Repair 1,'' this AD requires
replacing that text with ``767-200 SRM 53-10-01 Repair 1, 767-300
SRM 53-10-01 Repair 1, 767-300F SRM 53-10-01 Repair 1, 767-400 SRM
53-10-01 Repair 1, or B767-300BCF SRM 53-10-01 Repair 1, as
applicable.''
(4) Where Boeing Alert Requirements Bulletin 767-53A0301 RB,
Revision 2, dated May 24, 2023, refers to ``767-200 SRM 53-10-01
Repair 1, 767-300 SRM 53-10-01 Repair 1, or 767-400 SRM 53-10-01
Repair 1,'' this AD requires replacing that text with ``767-200 SRM
53-10-01 Repair 1, 767-300 SRM 53-10-01 Repair 1, 767-400 SRM 53-10-
01 Repair 1, or B767-300BCF SRM 53-10-01 Repair 1, as applicable.''
(i) Required Actions: Model 767-2C
At the later of the times specified in paragraphs (i)(1) and (2)
of this AD: Perform inspections (external detailed, internal
detailed, and open hole high frequency eddy current, as applicable),
including repetitive inspections as applicable, for cracking at the
forward entry door and forward service door cutout aft lower corner
fuselage skin and bear strap area, and repair any cracks found, in
accordance with a method and at the times specified, as approved by
the Manager, AIR-520, Continued Operational Safety Branch, FAA.
Note 2 to paragraph (i): Guidance on doing the required actions
can be found in Boeing Alert Requirements Bulletin 767-53A0303 RB,
Revision 1, dated June 29, 2023; and Boeing Alert Requirements
Bulletin 767-53A0308, Revision 1, dated June 21, 2023.
(1) Before 15,000 cumulative flight cycles or 30,000 cumulative
total accumulated cycles, whichever occurs first. These terms are
defined in paragraph (j) of this AD.
(2) Within 2,250 flight cycles, 4,500 total accumulated cycles,
or 24 months after the effective date of this AD, whichever occurs
first.
(j) Compliance Time Definitions for Model 767-2C
The definitions in paragraphs (j)(1) through (5) of this AD
apply to this AD.
(1) A ``flight cycle'' is an operation by an aircraft that is
initially stopped on the ground, departs in flight, attains a
maximum above ground level (AGL) altitude greater than 5,000 feet
relative to the runway, lands on a runway, and stops on the ground.
A flight cycle may include one or more touch-and-go cycles.
(2) A ``touch-and-go cycle'' is an operation by an aircraft that
lands and departs on a runway without stopping or exiting the runway
and is immediately followed by a short flight with a maximum AGL
altitude of 5,000 feet relative to the runway.
(3) ``Total accumulated cycles'' is the sum of the accumulated
number of flight cycles, accumulated missed approaches, and the
accumulated number of touch-and-go cycles.
(4) A ``missed approach'' (or go-around) is an aircraft landing
approach that is discontinued and proceeded by a climb-out for any
reason without landing gear touching the runway and is either
immediately preceded by or immediately followed by a short flight
with a maximum AGL altitude of 5,000 feet relative to the runway.
Any flight operation not meeting this definition is considered a
flight cycle.
(5) ``Cumulative'' cycles are total cycles since new.
(k) Credit for Previous Actions
This paragraph provides credit for the actions specified in
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Boeing Alert Requirements Bulletin
767-53A0301 RB, dated April 21, 2021, or Boeing Alert Requirements
Bulletin 767-53A0301 RB, Revision 1, dated April 11, 2022.
(l) Alternative Methods of Compliance (AMOCs)
(1) The Manager, AIR-520, Continued Operational Safety 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
(m)(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, AIR-
520, Continued Operational Safety 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.
(m) Related Information
(1) For more information about this AD, contact Joseph Hodgin,
Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA
98198; phone: 206-231-3962; email: [email protected].
(2) Service information identified in this AD that is not
incorporated by reference is available at the address specified in
paragraph (n)(3) of this AD.
(n) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
[[Page 22932]]
(i) Boeing Alert Requirements Bulletin 767-53A0301 RB, Revision
2, dated May 24, 2023.
(ii) [Reserved]
(3) 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; website myboeingfleet.com.
(4) You may view service information that is incorporated by
reference 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.
(5) You may view this material at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].
Issued on February 29, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2024-06993 Filed 4-2-24; 8:45 am]
BILLING CODE 4910-13-P
