Proposed Rule2022-01014
Airworthiness Directives; The Boeing Company Airplanes
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
January 21, 2022
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
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 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.
Full Text
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<title>Federal Register, Volume 87 Issue 14 (Friday, January 21, 2022)</title>
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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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2022-01014]
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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).
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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:
<bullet> Federal eRulemaking Portal: Go to <a href="https://www.regulations.gov">https://www.regulations.gov</a>. Follow the instructions for submitting comments.
<bullet> Fax: 202-493-2251.
<bullet> 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.
<bullet> 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 <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. 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 <a href="https://www.regulations.gov">https://www.regulations.gov</a>
by searching for and locating Docket No. FAA-2021-1073.
Examining the AD Docket
You may examine the AD docket at <a href="https://www.regulations.gov">https://www.regulations.gov</a> 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:
<a href="/cdn-cgi/l/email-protection#7404110011065a1e15060e1b1916341215155a131b02"><span class="__cf_email__" data-cfemail="8dfde8f9e8ffa3e7ecfff7e2e0efcdebececa3eae2fb">[email protected]</span></a>.
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
<a href="https://www.regulations.gov">https://www.regulations.gov</a>, 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: <a href="/cdn-cgi/l/email-protection#364653425344185c57444c595b547650575718515940"><span class="__cf_email__" data-cfemail="d1a1b4a5b4a3ffbbb0a3abbebcb391b7b0b0ffb6bea7">[email protected]</span></a>. 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 <a href="https://www.regulations.gov">https://www.regulations.gov</a> 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.
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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: <a href="/cdn-cgi/l/email-protection#526b7f131c1f7f1e1313111d7f131f1d117f0037232737212621123433337c353d24"><span class="__cf_email__" data-cfemail="90a9bdd1deddbddcd1d1d3dfbdd1dddfd3bdc2f5e1e5f5e3e4e3d0f6f1f1bef7ffe6">[email protected]</span></a>.
(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: <a href="/cdn-cgi/l/email-protection#daaabfaebfa8f4b0bba8a0b5b7b89abcbbbbf4bdb5ac"><span class="__cf_email__" data-cfemail="f9899c8d9c8bd793988b8396949bb99f9898d79e968f">[email protected]</span></a>.
(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 <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. 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
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