Airworthiness Directives; The Boeing Company Airplanes, 3246-3250 [2022-01014]
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Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Proposed Rules
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 determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) 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:
■
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Bell Textron Inc.: Docket No. FAA–2022–
0006; Project Identifier AD–2021–01298–
R.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by March 7,
2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the following Bell
Textron Inc. helicopters certificated in any
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category, with a tailboom left hand fin spar
cap (spar cap) part number 212–030–447–117
installed.
(1) Model 205A and 205A–1 helicopters,
serial number (S/N) 30001 through 30065
inclusive, 30067 through 30165 inclusive,
30167 through 30187 inclusive, 30189
through 30296 inclusive, and 30298 through
30332 inclusive;
(2) Model 205B helicopters, S/N 30066,
30166, 30188, and 30297;
(3) Model 210 helicopters, all S/Ns;
(4) Model 212 helicopters, S/N 30502
through 30603 inclusive, 30611 through
30999 inclusive, 31101 through 31311
inclusive, 32101 through 32142 inclusive,
and 35001 through 35103 inclusive;
(5) Model 412 and 412EP helicopters, S/N
33001 through 33213 inclusive, 34001
through 34036 inclusive, 36001 through
36999 inclusive, 37002 through 37999
inclusive, 38001 through 38999 inclusive,
and 39101 through 39999 inclusive; and
(6) Model 412CF helicopters, S/N 46400
through 46499 inclusive.
(d) Subject
Joint Aircraft System Component (JASC)
Code 5302, Rotorcraft Tail Boom.
(e) Unsafe Condition
This AD was prompted by the discovery of
fatigue cracking in the spar cap. A crack in
the spar cap, if not detected and corrected,
could create stress concentrations at the edge
of the rivet holes, resulting in reduced
structural integrity of the helicopter and
subsequent loss of control of the helicopter.
The FAA is issuing this AD to detect and
prevent this unsafe condition.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
Within 100 hours time-in-service (TIS)
after the effective date of this AD, and
thereafter at intervals not to exceed 100 hours
TIS:
(1) Using a 10x or higher power magnifying
glass and a flashlight, inspect both flanges of
the spar cap between fin station (F.S.) 50 and
F.S. 71 for any crack, loose rivet, and other
damage such as a scratch, dent, spalling, or
corrosion, as depicted in Figure 1 of Bell
Alert Service Bulletin (ASB) 205–20–116,
ASB 205B–20–69, ASB 210–20–13, ASB 212–
20–162, ASB 412–20–180, or ASB 412CF–
20–67, each dated April 15, 2020, as
applicable to your helicopter. If either spar
cap flange is cracked, has a loose rivet, or has
other damage, remove the spar cap from
service before further flight.
(2) Inspect the exterior of the fin skin in the
area that contacts the spar cap for any crack,
loose rivets, and distortion. If there is any
crack, loose rivet, or distortion in the fin skin
in the area that contacts the spar cap, remove
the spar cap from service before further
flight.
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, DSCO Branch, FAA, has
the authority to approve AMOCs for this AD,
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if requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the certification office,
send it to the attention of the person
identified in Related Information.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(i) Related Information
(1) For more information about this AD,
contact Ameet Shrotriya, Aviation Safety
Engineer, DSCO Branch, Compliance &
Airworthiness Division, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177–
1524; phone: (817) 222–5525; email:
Ameet.Shrotriya@faa.gov.
(2) For service information identified in
this AD, contact Bell Textron, Inc., P.O. Box
482, Fort Worth, TX 76101; telephone 1–450–
437–2862 or 1–800–363–8023; fax 1–450–
433–0272; email productsupport@
bellflight.com; or at https://
www.bellflight.com/support/contact-support.
You may view this referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region, 10101
Hillwood Pkwy., Room 6N–321, Fort Worth,
TX 76177. For information on the availability
of this material at the FAA, call (817) 222–
5110.
Issued on January 11, 2022.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2022–00886 Filed 1–20–22; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–1073; Project
Identifier AD–2021–01252–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)
2017–24–10, which applies to certain
The Boeing Company Model 757–200,
–200PF, and –300 series airplanes. AD
2017–24–10 requires repetitive
inspections for any cracking of a certain
fuselage frame inner chord;
identification of the material of a certain
fuselage frame inner chord for certain
SUMMARY:
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Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Proposed Rules
airplanes; and applicable corrective
actions. Since the FAA issued AD 2017–
24–10, the FAA has received reports of
new crack findings outside of the AD
2017–24–10 inspection area, which the
existing inspections will not detect.
This proposed AD would continue to
require the actions in AD 2017–24–10,
would add new airplanes and would
require new inspection types in certain
areas, an expanded inspection area,
additional inspections, and applicable
corrective actions. The FAA is
proposing this AD to address the unsafe
condition on these products.
DATES: The FAA must receive comments
on this proposed AD by March 7, 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
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster
Blvd., MC 110–SK57, Seal Beach, CA
90740–5600; telephone 562–797–1717;
internet https://
www.myboeingfleet.com. You may view
this 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 https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
1073.
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Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–1073; 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:
Peter Jarzomb, Aerospace Engineer,
Airframe Section, FAA, Los Angeles
ACO Branch, 3960 Paramount
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Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5234; email:
peter.jarzomb@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under ADDRESSES. Include ‘‘Docket No.
FAA–2021–1073; Project Identifier AD–
2021–01252–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 https://
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 Peter Jarzomb,
Aerospace Engineer, Airframe Section,
FAA, Los Angeles ACO Branch, 3960
Paramount Boulevard, Lakewood, CA
90712–4137; phone: 562–627–5234;
email: peter.jarzomb@faa.gov. Any
commentary that the FAA receives
which is not specifically designated as
CBI will be placed in the public docket
for this rulemaking.
Background
The FAA issued AD 2017–24–10,
Amendment 39–19114 (82 FR 57343,
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3247
December 5, 2017) (AD 2017–24–10), for
certain The Boeing Company Model
757–200, –200PF, and –300 series
airplanes. AD 2017–24–10 was
prompted by reports of cracking found
at a certain fuselage frame inner chord.
AD 2017–24–10 requires repetitive
inspections for any cracking of a certain
fuselage frame inner chord;
identification of the material of a certain
fuselage frame inner chord for certain
airplanes; and applicable corrective
actions. The agency issued AD 2017–
24–10 to detect and correct such cracks,
which could result in the cargo door
opening during flight, and result in
rapid decompression of the airplane and
the inability to sustain loads required
for continued safe flight and landing.
Actions Since AD 2017–24–10 Was
Issued
Since the FAA issued AD 2017–24–
10, the FAA has received reports of new
crack findings outside of the AD 2017–
24–10 inspection area, which the
existing inspections will not detect. An
operator was accomplishing Boeing
Alert Service Bulletin 757–53A0101,
dated November 8, 2016, which is the
service information required by AD
2017–24–10) on a certain The Boeing
Company Model 757–200 airplane and
found four cracks ranging from 0.10 to
2.00 inches in length in the station
(STA) 1380 frame web and two cracks
ranging from 1.00 to 2.12 inches in
length in the frame inner chord. The
airplane had 23,005 total flight cycles at
the time of the crack findings. The frame
web was made from 0.09 inch thick
2024–T3 aluminum, and the inner
chord was made from 7075–T73
aluminum. Based on the length of the
crack in the web at the time of
discovery, the cracks in the frame may
have initiated in the 2024–T3 web, and
would have been hidden behind the
guide track fitting. If the cracks start in
the frame web, existing Maintenance
Planning Data (MPD) and Boeing Alert
Service Bulletin 757–53A0101, dated
November 8, 2016, inspections do not
provide sufficient opportunities to find
cracks in the STA 1380 frame before the
critical crack length is reached, resulting
in an airplane-level safety issue.
In addition, the FAA has received five
reports of crack findings in airplanes
with production line numbers 1–57,
which are made with 7075 material for
the inner and outer chord and the frame
web. Those airplanes may also have a
thinner web gauge than that in airplanes
with line numbers 58 and subsequent.
Existing inspections for these airplanes
do not remove the guide track fitting at
STA 1380, and therefore do not provide
sufficient opportunity to detect cracks
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Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Proposed Rules
before the critical crack length is
reached.
The root cause for the cracking in the
STA 1380 frame inner chord and web
under the roller guide track fitting is
attributed to the out-of-plane bending
stress induced from a mis-rigging
condition of the No. 2 cargo door, which
allows the roller pin on the lower cargo
door to contact the roller guide track
fitting. The new proposed repetitive
inspections include removing the guide
track fitting to inspect for any crack. The
FAA is issuing this AD to detect and
correct such cracks, which could result
in rapid decompression of the airplane
and the inability to sustain loads
required for continued safe flight and
landing.
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
Requirements Bulletin 757–53A0118
RB, dated October 22, 2021. This service
information specifies procedures for a
general visual inspection or a
maintenance records check of the STA
1380 frame for any repair, and repetitive
surface high frequency eddy current
(HFEC) inspections of the STA 1380
frame inner chord and frame web for
any cracking, repetitive sub-surface low
frequency eddy current (LFEC)
inspections of the STA 1380 frame inner
chord for any cracking, and applicable
corrective actions. Corrective actions
include repair.
This AD would also require Boeing
Alert Service Bulletin 757–53A0101,
dated November 8, 2016, which the
Director of the Federal Register
approved for incorporation by reference
as of January 9, 2018 (82 FR 57343,
December 5, 2017).
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
area, additional inspections, and
applicable corrective actions. This
proposed AD would require
accomplishment of the actions
identified in Boeing Alert Requirements
Bulletin 757–53A0118 RB, dated
October 22, 2021, described previously,
except for any differences identified as
exceptions in the regulatory text of this
proposed AD.
Accomplishment of the applicable
initial inspections and corrective
actions specified in the
Accomplishment Instructions of Boeing
Alert Requirements Bulletin 757–
53A0118 RB, dated October 22, 2021,
terminates the inspections required by
paragraphs (g) and (h) of this proposed
AD.
For information on the procedures
and compliance times, see this service
information at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
1073.
Costs of Compliance
This proposed AD would retain all
requirements of AD 2017–24–10. This
proposed AD would add new airplanes
and would require new inspection types
in certain areas, an expanded inspection
The FAA estimates that this AD, if
adopted as proposed, would affect 477
airplanes of U.S. registry. The FAA
estimates the following costs to comply
with this proposed AD:
ESTIMATED COSTS
Cost on U.S. operators
0
$425 per inspection
cycle.
Up to $170 ....................
$202,725 per inspection
cycle.
Up to $81,090.
0
$510 ..............................
$243,270.
0
Up to $850 per inspection cycle.
Up to $510 per inspection cycle.
Up to $405,450 per inspection cycle.
Up to $243,270 per inspection cycle.
Up to $510 per inspection cycle.
Up to $243,270 per inspection cycle.
Labor cost
Surface HFEC inspection (retained
actions from AD 2017–24–10).
Identify the material (retained actions from AD 2017–24–10).
General visual inspection (new proposed action).
Surface frame inner chord HFEC
inspection (new proposed action).
Sub-surface frame inner chord
LFEC inspection (new proposed
action).
Surface HFEC frame web inspection (new proposed action).
5 work-hours × $85 per hour =
$425 per inspection cycle.
Up to 2 work-hours × $85 per hour
= $170.
6 work-hours × $85 per hour =
$510.
Up to 10 work-hours × $85 per
hour = $850 per inspection cycle.
Up to 6 work-hours × $85 per hour
= $510 per inspection cycle.
$0
Up to 6 work-hours × $85 per hour
= $510 per inspection cycle.
0
The FAA has received no definitive
data on which to base the cost estimates
for the on-condition repairs specified in
this proposed AD.
Authority for This Rulemaking
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Cost per
product
Action
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
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Parts cost
0
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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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,
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Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Proposed Rules
(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:
a. Removing Airworthiness Directive
(AD) 2017–24–10, Amendment 39–
19114 (82 FR 57343, December 5, 2017),
and
■ b. Adding the following new AD:
■
■
The Boeing Company: Docket No. FAA–
2021–1073; Project Identifier AD–2021–
01252–T.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) action by March
7, 2022.
(b) Affected ADs
This AD replaces AD 2017–24–10,
Amendment 39–19114 (82 FR 57343,
December 5, 2017) (AD 2017–24–10).
(c) Applicability
This AD applies to all The Boeing
Company Model 757–200, –200PF, –200CB,
and –300 series airplanes, certificated in any
category.
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(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of
cracking found at the fuselage station (STA)
1380 frame inner chord and by reports of
new crack findings outside of the AD 2017–
24–10 inspection area, which the existing
inspections will not detect. The FAA is
issuing this AD to detect and correct such
cracks, which could result in rapid
decompression of the airplane and the
inability to sustain loads required for
continued safe flight and landing.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Retained Inspection for Group 1
Airplanes, With No Changes
This paragraph restates the requirements of
paragraph (g) of AD 2017–24–10, with no
changes. For Group 1 airplanes as identified
in Boeing Alert Service Bulletin 757–
53A0101, dated November 8, 2016: At the
applicable time specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 757–53A0101, dated November 8,
2016; except as specified in paragraph (i)(1)
of this AD, do a surface high frequency eddy
current (HFEC) inspection for any cracking of
the fuselage STA 1380 frame inner chord,
and do all applicable corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
757–53A0101, dated November 8, 2016;
except as specified in paragraph (i)(2) of this
AD. Do all applicable corrective actions
before further flight. Repeat the surface HFEC
inspection, thereafter, at the times specified
in paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 757–53A0101, dated
November 8, 2016.
(h) Retained Inspection for Group 2
Airplanes, With No Changes
This paragraph restates the requirements of
paragraph (h) of AD 2017–24–10, with no
changes. For Group 2 airplanes as identified
in Boeing Alert Service Bulletin 757–
53A0101, dated November 8, 2016: At the
applicable time specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 757–53A0101, dated November 8,
2016, except as specified in paragraph (i)(1)
of this AD, identify the material of the
fuselage STA 1380 frame inner chord, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
757–53A0101, dated November 8, 2016.
(1) If the fuselage STA 1380 frame inner
chord material 2024–T42 aluminum alloy is
found during any identification required by
paragraph (h) of this AD: No further action
is required by this paragraph for that
airplane.
(2) If the fuselage STA 1380 frame inner
chord material 7075–T73 aluminum alloy is
found during any identification required by
the introductory text of paragraph (h) of this
AD: Before further flight, do a surface HFEC
inspection for any cracking of the fuselage
STA 1380 frame inner chord, and do all
applicable corrective actions, in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 757–53A0101,
dated November 8, 2016; except as specified
in paragraph (i)(2) of this AD. Do all
applicable corrective actions before further
flight. Repeat the surface HFEC inspection
thereafter at the times specified in paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 757–53A0101, dated November 8,
2016.
(i) Retained Exceptions to the Service
Information, With No Changes
This paragraph restates the requirements of
paragraph (i) of AD 2017–24–10, with no
changes.
(1) Where Boeing Alert Service Bulletin
757–53A0101, dated November 8, 2016,
specifies a compliance time ‘‘after the
original issue date of this service bulletin,’’
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3249
this AD requires compliance within the
specified compliance time after January 9,
2018 (the effective date of AD 2017–24–10).
(2) Where Boeing Alert Service Bulletin
757–53A0101, dated November 8, 2016,
specifies to contact Boeing for appropriate
action and identifies that action as ‘‘RC’’
(Required for Compliance): Before further
flight, repair the crack using a method
approved in accordance with the procedures
specified in paragraph (m) of this AD.
(j) New Required Actions
Except as specified by paragraph (k) of this
AD: At the applicable times specified in the
‘‘Compliance’’ paragraph of Boeing Alert
Requirements Bulletin 757–53A0118 RB,
dated October 22, 2021, do all applicable
actions identified in, and in accordance with,
the Accomplishment Instructions of Boeing
Alert Requirements Bulletin 757–53A0118
RB, dated October 22, 2021.
Note 1 to paragraph (j): Guidance for
accomplishing the actions required by this
AD can be found in Boeing Alert Service
Bulletin 757–53A0118, dated October 22,
2021, which is referred to in Boeing Alert
Requirements Bulletin 757–53A0118 RB,
dated October 22, 2021.
(k) New Exceptions to Service Information
Specifications
(1) Where the Compliance Time column of
the tables in the ‘‘Compliance’’ paragraph of
Boeing Alert Requirements Bulletin 757–
53A0118 RB, dated October 22, 2021, uses
the phrase ‘‘the original issue date of the
Requirements Bulletin 757–53A0118 RB,’’
this AD requires using ‘‘the effective date of
this AD.’’
(2) Where Boeing Alert Requirements
Bulletin 757–53A0118 RB, dated October 22,
2021, specifies contacting Boeing for repair
instructions or for alternative inspections:
This AD requires doing the repair, or doing
the alternative inspections and applicable oncondition actions using a method approved
in accordance with the procedures specified
in paragraph (m) of this AD.
(l) Terminating Action for Certain
Inspections
Accomplishment of the applicable initial
inspections and corrective actions specified
in the Accomplishment Instructions of
Boeing Alert Requirements Bulletin 757–
53A0118 RB, dated October 22, 2021,
terminates the inspections required by
paragraphs (g) and (h) of this AD.
(m) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles ACO Branch,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with
14 CFR 39.19, send your request to your
principal inspector or 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 (n)(1) of
this AD. Information may be emailed to: 9ANM-LAACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
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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, Los Angeles ACO Branch, FAA, to
make those findings. To be approved, the
repair method, modification deviation, or
alteration deviation must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved previously for AD
2017–24–10 are not approved as AMOCs
with this AD.
(5) Except as specified by paragraph (i) of
this AD: For service information that
contains steps that are labeled as Required
for Compliance (RC), the provisions of
paragraphs (m)(5)(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.
DEPARTMENT OF HEALTH AND
HUMAN SERVICES
Food and Drug Administration
21 CFR Part 866
[Docket No. FDA–2021–N–0851]
Medical Devices; Immunology and
Microbiology Devices; Classification of
Human Leukocyte, Neutrophil and
Platelet Antigen and Antibody Tests
AGENCY:
Food and Drug Administration,
HHS.
ACTION:
Proposed rule.
The Food and Drug
Administration (FDA, the Agency, or
we) is proposing to classify Human
Leukocyte Antigen (HLA), Human
Platelet Antigen (HPA), and Human
Neutrophil Antigen (HNA) devices, a
generic type of device, into class II
(special controls). FDA is identifying
proposed special controls for HLA,
HPA, and HNA devices that are
necessary to provide a reasonable
assurance of safety and effectiveness.
FDA is also giving notice that we do not
intend to exempt these device types
from premarket notification
requirements of the Federal Food, Drug,
and Cosmetic Act (FD&C Act). FDA is
publishing in this document the
recommendations of the Blood Products
Advisory Committee, serving as a device
classification panel, regarding the
classification of these devices. After
considering public comments on the
(n) Related Information
proposed classification, FDA will
(1) For more information about this AD,
publish a final regulation classifying
contact Peter Jarzomb, Aerospace Engineer,
these device types.
Airframe Section, FAA, Los Angeles ACO
DATES: Submit either electronic or
Branch, 3960 Paramount Boulevard,
written comments on the proposed rule
Lakewood, CA 90712–4137; phone: 562–627–
by April 21, 2022.
5234; email: peter.jarzomb@faa.gov.
ADDRESSES
: You may submit comments
(2) For service information identified in
as follows. Please note that late,
this AD, contact Boeing Commercial
untimely filed comments will not be
Airplanes, Attention: Contractual & Data
considered. Electronic comments must
Services (C&DS), 2600 Westminster Blvd.,
be submitted on or before April 21,
MC 110–SK57, Seal Beach, CA 90740–5600;
2022. The https://www.regulations.gov
telephone 562–797–1717; internet https://
electronic filing system will accept
www.myboeingfleet.com. You may view this
comments until 11:59 p.m. Eastern Time
referenced service information at the FAA,
at the end of April 21, 2022. Comments
Airworthiness Products Section, Operational
received by mail/hand delivery/courier
Safety Branch, 2200 South 216th St., Des
(for written/paper submissions) will be
Moines, WA. For information on the
considered timely if they are
availability of this material at the FAA, call
postmarked or the delivery service
206–231–3195.
acceptance receipt is on or before that
Issued on December 10, 2021.
date.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2022–01014 Filed 1–20–22; 8:45 am]
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SUMMARY:
Electronic Submissions
Submit electronic comments in the
following way:
• Federal eRulemaking Portal:
https://www.regulations.gov. Follow the
instructions for submitting comments.
Comments submitted electronically,
PO 00000
Frm 00022
Fmt 4702
Sfmt 4702
including attachments, to https://
www.regulations.gov will be posted to
the docket unchanged. Because your
comment will be made public, you are
solely responsible for ensuring that your
comment does not include any
confidential information that you or a
third party may not wish to be posted,
such as medical information, your or
anyone else’s Social Security number, or
confidential business information, such
as a manufacturing process. Please note
that if you include your name, contact
information, or other information that
identifies you in the body of your
comments, that information will be
posted on https://www.regulations.gov.
• If you want to submit a comment
with confidential information that you
do not wish to be made available to the
public, submit the comment as a
written/paper submission and in the
manner detailed (see ‘‘Written/Paper
Submissions’’ and ‘‘Instructions’’).
Written/Paper Submissions
Submit written/paper submissions as
follows:
• Mail/Hand Delivery/Courier (for
written/paper submissions): Dockets
Management Staff (HFA–305), Food and
Drug Administration, 5630 Fishers
Lane, Rm. 1061, Rockville, MD 20852.
• For written/paper comments
submitted to the Dockets Management
Staff, FDA will post your comment, as
well as any attachments, except for
information submitted, marked and
identified, as confidential, if submitted
as detailed in ‘‘Instructions.’’
Instructions: All submissions received
must include the Docket No. FDA–
2021–N–0851 for ‘‘Medical Devices;
Immunology and Microbiology
Classification of Human Leukocyte,
Neutrophil and Platelet Antigen and
Antibody Tests.’’ Received comments,
those filed in a timely manner (see
ADDRESSES), will be placed in the docket
and, except for those submitted as
‘‘Confidential Submissions,’’ publicly
viewable at https://www.regulations.gov
or at the Dockets Management Staff
between 9 a.m. and 4 p.m., Monday
through Friday, 240–402–7500.
• Confidential Submissions—To
submit a comment with confidential
information that you do not wish to be
made publicly available, submit your
comments only as a written/paper
submission. You should submit two
copies total. One copy will include the
information you claim to be confidential
with a heading or cover note that states
‘‘THIS DOCUMENT CONTAINS
CONFIDENTIAL INFORMATION.’’ The
Agency will review this copy, including
the claimed confidential information, in
its consideration of comments. The
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[Federal Register Volume 87, Number 14 (Friday, January 21, 2022)]
[Proposed Rules]
[Pages 3246-3250]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-01014]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-1073; Project Identifier AD-2021-01252-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)
2017-24-10, which applies to certain The Boeing Company Model 757-200,
-200PF, and -300 series airplanes. AD 2017-24-10 requires repetitive
inspections for any cracking of a certain fuselage frame inner chord;
identification of the material of a certain fuselage frame inner chord
for certain
[[Page 3247]]
airplanes; and applicable corrective actions. Since the FAA issued AD
2017-24-10, the FAA has received reports of new crack findings outside
of the AD 2017-24-10 inspection area, which the existing inspections
will not detect. This proposed AD would continue to require the actions
in AD 2017-24-10, would add new airplanes and would require new
inspection types in certain areas, an expanded inspection area,
additional inspections, and applicable corrective actions. The FAA is
proposing this AD to address the unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by March 7,
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 https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Boeing
Commercial Airplanes, Attention: Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600;
telephone 562-797-1717; internet https://www.myboeingfleet.com. You may
view this 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 https://www.regulations.gov
by searching for and locating Docket No. FAA-2021-1073.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-1073; 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: Peter Jarzomb, Aerospace Engineer,
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5234; email:
[email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2021-1073; Project Identifier
AD-2021-01252-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
https://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 Peter
Jarzomb, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO
Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-
627-5234; email: [email protected]. Any commentary that the FAA
receives which is not specifically designated as CBI will be placed in
the public docket for this rulemaking.
Background
The FAA issued AD 2017-24-10, Amendment 39-19114 (82 FR 57343,
December 5, 2017) (AD 2017-24-10), for certain The Boeing Company Model
757-200, -200PF, and -300 series airplanes. AD 2017-24-10 was prompted
by reports of cracking found at a certain fuselage frame inner chord.
AD 2017-24-10 requires repetitive inspections for any cracking of a
certain fuselage frame inner chord; identification of the material of a
certain fuselage frame inner chord for certain airplanes; and
applicable corrective actions. The agency issued AD 2017-24-10 to
detect and correct such cracks, which could result in the cargo door
opening during flight, and result in rapid decompression of the
airplane and the inability to sustain loads required for continued safe
flight and landing.
Actions Since AD 2017-24-10 Was Issued
Since the FAA issued AD 2017-24-10, the FAA has received reports of
new crack findings outside of the AD 2017-24-10 inspection area, which
the existing inspections will not detect. An operator was accomplishing
Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016,
which is the service information required by AD 2017-24-10) on a
certain The Boeing Company Model 757-200 airplane and found four cracks
ranging from 0.10 to 2.00 inches in length in the station (STA) 1380
frame web and two cracks ranging from 1.00 to 2.12 inches in length in
the frame inner chord. The airplane had 23,005 total flight cycles at
the time of the crack findings. The frame web was made from 0.09 inch
thick 2024-T3 aluminum, and the inner chord was made from 7075-T73
aluminum. Based on the length of the crack in the web at the time of
discovery, the cracks in the frame may have initiated in the 2024-T3
web, and would have been hidden behind the guide track fitting. If the
cracks start in the frame web, existing Maintenance Planning Data (MPD)
and Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016,
inspections do not provide sufficient opportunities to find cracks in
the STA 1380 frame before the critical crack length is reached,
resulting in an airplane-level safety issue.
In addition, the FAA has received five reports of crack findings in
airplanes with production line numbers 1-57, which are made with 7075
material for the inner and outer chord and the frame web. Those
airplanes may also have a thinner web gauge than that in airplanes with
line numbers 58 and subsequent. Existing inspections for these
airplanes do not remove the guide track fitting at STA 1380, and
therefore do not provide sufficient opportunity to detect cracks
[[Page 3248]]
before the critical crack length is reached.
The root cause for the cracking in the STA 1380 frame inner chord
and web under the roller guide track fitting is attributed to the out-
of-plane bending stress induced from a mis-rigging condition of the No.
2 cargo door, which allows the roller pin on the lower cargo door to
contact the roller guide track fitting. The new proposed repetitive
inspections include removing the guide track fitting to inspect for any
crack. The FAA is issuing this AD to detect and correct such cracks,
which could result in rapid decompression of the airplane and the
inability to sustain loads required for continued safe flight and
landing.
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 Requirements Bulletin 757-53A0118 RB,
dated October 22, 2021. This service information specifies procedures
for a general visual inspection or a maintenance records check of the
STA 1380 frame for any repair, and repetitive surface high frequency
eddy current (HFEC) inspections of the STA 1380 frame inner chord and
frame web for any cracking, repetitive sub-surface low frequency eddy
current (LFEC) inspections of the STA 1380 frame inner chord for any
cracking, and applicable corrective actions. Corrective actions include
repair.
This AD would also require Boeing Alert Service Bulletin 757-
53A0101, dated November 8, 2016, which the Director of the Federal
Register approved for incorporation by reference as of January 9, 2018
(82 FR 57343, December 5, 2017).
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
This proposed AD would retain all requirements of AD 2017-24-10.
This proposed AD would add new airplanes and would require new
inspection types in certain areas, an expanded inspection area,
additional inspections, and applicable corrective actions. This
proposed AD would require accomplishment of the actions identified in
Boeing Alert Requirements Bulletin 757-53A0118 RB, dated October 22,
2021, described previously, except for any differences identified as
exceptions in the regulatory text of this proposed AD.
Accomplishment of the applicable initial inspections and corrective
actions specified in the Accomplishment Instructions of Boeing Alert
Requirements Bulletin 757-53A0118 RB, dated October 22, 2021,
terminates the inspections required by paragraphs (g) and (h) of this
proposed AD.
For information on the procedures and compliance times, see this
service information at https://www.regulations.gov by searching for and
locating Docket No. FAA-2021-1073.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 477 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
----------------------------------------------------------------------------------------------------------------
Surface HFEC inspection (retained 5 work-hours x $85 $0 $425 per inspection $202,725 per
actions from AD 2017-24-10). per hour = $425 cycle. inspection cycle.
per inspection
cycle.
Identify the material (retained Up to 2 work-hours 0 Up to $170......... Up to $81,090.
actions from AD 2017-24-10). x $85 per hour =
$170.
General visual inspection (new 6 work-hours x $85 0 $510............... $243,270.
proposed action). per hour = $510.
Surface frame inner chord HFEC Up to 10 work-hours 0 Up to $850 per Up to $405,450 per
inspection (new proposed action). x $85 per hour = inspection cycle. inspection cycle.
$850 per
inspection cycle.
Sub-surface frame inner chord Up to 6 work-hours 0 Up to $510 per Up to $243,270 per
LFEC inspection (new proposed x $85 per hour = inspection cycle. inspection cycle.
action). $510 per
inspection cycle.
Surface HFEC frame web inspection Up to 6 work-hours 0 Up to $510 per Up to $243,270 per
(new proposed action). x $85 per hour = inspection cycle. inspection cycle.
$510 per
inspection cycle.
----------------------------------------------------------------------------------------------------------------
The FAA has received no definitive data on which to base the cost
estimates for the on-condition repairs specified in this proposed AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
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,
[[Page 3249]]
(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
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) 2017-24-10, Amendment 39-19114
(82 FR 57343, December 5, 2017), and
0
b. Adding the following new AD:
The Boeing Company: Docket No. FAA-2021-1073; Project Identifier AD-
2021-01252-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) action by March 7, 2022.
(b) Affected ADs
This AD replaces AD 2017-24-10, Amendment 39-19114 (82 FR 57343,
December 5, 2017) (AD 2017-24-10).
(c) Applicability
This AD applies to all The Boeing Company Model 757-200, -200PF,
-200CB, and -300 series airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of cracking found at the
fuselage station (STA) 1380 frame inner chord and by reports of new
crack findings outside of the AD 2017-24-10 inspection area, which
the existing inspections will not detect. The FAA is issuing this AD
to detect and correct such cracks, which could result in rapid
decompression of the airplane and the inability to sustain loads
required for continued safe flight and landing.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspection for Group 1 Airplanes, With No Changes
This paragraph restates the requirements of paragraph (g) of AD
2017-24-10, with no changes. For Group 1 airplanes as identified in
Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016:
At the applicable time specified in paragraph 1.E., ``Compliance,''
of Boeing Alert Service Bulletin 757-53A0101, dated November 8,
2016; except as specified in paragraph (i)(1) of this AD, do a
surface high frequency eddy current (HFEC) inspection for any
cracking of the fuselage STA 1380 frame inner chord, and do all
applicable corrective actions, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 757-53A0101, dated
November 8, 2016; except as specified in paragraph (i)(2) of this
AD. Do all applicable corrective actions before further flight.
Repeat the surface HFEC inspection, thereafter, at the times
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 757-53A0101, dated November 8, 2016.
(h) Retained Inspection for Group 2 Airplanes, With No Changes
This paragraph restates the requirements of paragraph (h) of AD
2017-24-10, with no changes. For Group 2 airplanes as identified in
Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016:
At the applicable time specified in paragraph 1.E., ``Compliance,''
of Boeing Alert Service Bulletin 757-53A0101, dated November 8,
2016, except as specified in paragraph (i)(1) of this AD, identify
the material of the fuselage STA 1380 frame inner chord, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 757-53A0101, dated November 8, 2016.
(1) If the fuselage STA 1380 frame inner chord material 2024-T42
aluminum alloy is found during any identification required by
paragraph (h) of this AD: No further action is required by this
paragraph for that airplane.
(2) If the fuselage STA 1380 frame inner chord material 7075-T73
aluminum alloy is found during any identification required by the
introductory text of paragraph (h) of this AD: Before further
flight, do a surface HFEC inspection for any cracking of the
fuselage STA 1380 frame inner chord, and do all applicable
corrective actions, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 757-53A0101, dated
November 8, 2016; except as specified in paragraph (i)(2) of this
AD. Do all applicable corrective actions before further flight.
Repeat the surface HFEC inspection thereafter at the times specified
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
757-53A0101, dated November 8, 2016.
(i) Retained Exceptions to the Service Information, With No Changes
This paragraph restates the requirements of paragraph (i) of AD
2017-24-10, with no changes.
(1) Where Boeing Alert Service Bulletin 757-53A0101, dated
November 8, 2016, specifies a compliance time ``after the original
issue date of this service bulletin,'' this AD requires compliance
within the specified compliance time after January 9, 2018 (the
effective date of AD 2017-24-10).
(2) Where Boeing Alert Service Bulletin 757-53A0101, dated
November 8, 2016, specifies to contact Boeing for appropriate action
and identifies that action as ``RC'' (Required for Compliance):
Before further flight, repair the crack using a method approved in
accordance with the procedures specified in paragraph (m) of this
AD.
(j) New Required Actions
Except as specified by paragraph (k) of this AD: At the
applicable times specified in the ``Compliance'' paragraph of Boeing
Alert Requirements Bulletin 757-53A0118 RB, dated October 22, 2021,
do all applicable actions identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Requirements Bulletin
757-53A0118 RB, dated October 22, 2021.
Note 1 to paragraph (j): Guidance for accomplishing the actions
required by this AD can be found in Boeing Alert Service Bulletin
757-53A0118, dated October 22, 2021, which is referred to in Boeing
Alert Requirements Bulletin 757-53A0118 RB, dated October 22, 2021.
(k) New Exceptions to Service Information Specifications
(1) Where the Compliance Time column of the tables in the
``Compliance'' paragraph of Boeing Alert Requirements Bulletin 757-
53A0118 RB, dated October 22, 2021, uses the phrase ``the original
issue date of the Requirements Bulletin 757-53A0118 RB,'' this AD
requires using ``the effective date of this AD.''
(2) Where Boeing Alert Requirements Bulletin 757-53A0118 RB,
dated October 22, 2021, 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 (m) of this AD.
(l) Terminating Action for Certain Inspections
Accomplishment of the applicable initial inspections and
corrective actions specified in the Accomplishment Instructions of
Boeing Alert Requirements Bulletin 757-53A0118 RB, dated October 22,
2021, terminates the inspections required by paragraphs (g) and (h)
of this AD.
(m) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles ACO Branch, FAA, has the authority
to approve AMOCs for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your
request to your principal inspector or 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 (n)(1) of this AD. Information may be
emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector,
[[Page 3250]]
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, Los
Angeles ACO Branch, FAA, to make those findings. To be approved, the
repair method, modification deviation, or alteration deviation must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved previously for AD 2017-24-10 are not approved
as AMOCs with this AD.
(5) Except as specified by paragraph (i) of this AD: For service
information that contains steps that are labeled as Required for
Compliance (RC), the provisions of paragraphs (m)(5)(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.
(n) Related Information
(1) For more information about this AD, contact Peter Jarzomb,
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5234; email: [email protected].
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this referenced service
information at the FAA, 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 December 10, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2022-01014 Filed 1-20-22; 8:45 am]
BILLING CODE 4910-13-P
