[Federal Register Volume 87, Number 180 (Monday, September 19, 2022)]
[Proposed Rules]
[Pages 57155-57158]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-19960]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-1054; Project Identifier AD-2022-00278-T]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2017-18-05, which applies to all The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 
747-400D, 747-400F, 747SR, and 747SP series airplanes. AD 2017-18-05 
requires repetitive replacement or inspection of certain fuse pins, and 
applicable on-condition actions. Since the FAA issued AD 2017-18-05, it 
has been determined that adding repetitive ultrasonic testing (UT) 
inspections of the fuse pin of the wing landing gear beam end fitting 
for any cracking and the option for repetitive replacement of certain 
corrosion-resistant (stainless) steel (CRES) fuse pins and steel alloy 
fuse pins is necessary to address the

[[Page 57156]]

unsafe condition. This proposed AD would continue to require the 
actions in AD 2017-18-05 and would also require repetitive replacement 
of certain fuse pins at the wing landing gear beam end fitting, and 
repetitive inspections of the fuse pin for any cracking and applicable 
on-condition actions. This proposed AD would also revise the 
applicability by adding airplanes. The FAA is proposing this AD to 
address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by November 3, 
2022.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to www.regulations.gov. 
Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Boeing 
Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; 
telephone 562-797-1717; internet www.myboeingfleet.com. You may view 
this service information at the FAA, Airworthiness Products Section, 
Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 206-
231-3195. It is also available at www.regulations.gov by searching for 
and locating Docket No. FAA-2022-1054.

Examining the AD Docket

    You may examine the AD docket at www.regulations.gov by searching 
for and locating Docket No. FAA-2022-1054; or in person at Docket 
Operations between 9 a.m. and 5 p.m., Monday through Friday, except 
Federal holidays. The AD docket contains this NPRM, any comments 
received, and other information. The street address for Docket 
Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Stefanie Roesli, Aerospace Engineer, 
Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des 
Moines, WA 98198; phone and fax: 206-231-3964; email: 
[email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2022-1054; Project Identifier 
AD-2022-00278-T'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
the proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
www.regulations.gov, including any personal information you provide. 
The agency will also post a report summarizing each substantive verbal 
contact received about this proposed AD.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this NPRM, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this NPRM. Submissions containing CBI should be sent to 
Stefanie Roesli, Aerospace Engineer, Airframe Section, FAA, Seattle ACO 
Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206-
231-3964; email: [email protected]. Any commentary that the FAA 
receives that is not specifically designated as CBI will be placed in 
the public docket for this rulemaking.

Background

    The FAA issued AD 2017-18-05; Amendment 39-19014 (82 FR 41331, 
August 31, 2017) (AD 2017-18-05), for all The Boeing Company Model 747-
100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 
747-400, 747-400D, 747-400F, 747SR, and 747SP airplanes. AD 2017-18-05 
was prompted by a report of damage found at the lower trailing edge 
panels of the left wing and a broken fuse pin of the landing gear beam 
end fitting. AD 2017-18-05 requires repetitive replacement or 
inspection of certain fuse pins, and applicable on-condition actions. 
The agency issued AD 2017-18-05 to detect and correct cracking in the 
fuse pin of the wing landing gear beam end fitting. A broken fuse pin 
will not support the wing landing gear beam, causing damage to the 
surrounding structure, including flight control cables and hydraulic 
systems, which could result in loss of controllability of the airplane.

Actions Since AD 2017-18-05 Was Issued

    Since the FAA issued AD 2017-18-05, it has been determined that 
adding repetitive UT inspections of the fuse pin of the wing landing 
gear beam end fitting for any cracking and the option for repetitive 
replacement of certain CRES fuse pins and steel alloy fuse pins is 
necessary to address the unsafe condition.
    In addition, Model 747-8F and 747-8 series airplanes have been 
added to the applicability. Analysis showed that Model 747-8F and 747-8 
series airplanes have a similar fuse pin in the same location as on 
Model 747-400 series airplanes, and these fuse pins are susceptible to 
fatigue cracks on the inner and outer surfaces.

FAA's Determination

    The FAA is issuing this NPRM after determining that the unsafe 
condition described previously is likely to exist or develop on other 
products of the same type design.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Boeing Alert Service Bulletin 747-57A2360, 
Revision 1, dated February 9, 2022. This service information specifies 
procedures for optional repetitive replacement of certain steel alloy 
fuse pins or CRES fuse pins with new or serviceable fuse pins, at the 
wing landing gear beam end fitting; and repetitive magnetic particle 
inspections, or repetitive surface high frequency eddy current (HFEC) 
and UT testing inspections, of the fuse pin of the wing landing gear 
beam end fitting for any cracking and corrosion and applicable on-
condition actions. On-condition actions includes replacing with steel 
alloy or CRES fuse pins, and doing magnetic particle, surface HFEC,

[[Page 57157]]

and UT testing inspections, and replacing cracked fuse pins.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Proposed AD Requirements in This NPRM

    Although this proposed AD does not explicitly restate the 
requirements of AD 2017-18-05, this proposed AD would retain all of the 
requirements of AD 2017-18-05. Those requirements are referenced in the 
service information identified previously, which, in turn, is 
referenced in paragraph (g) of this proposed AD. This proposed AD would 
add airplanes to the applicability. This proposed AD would also require 
accomplishment of the actions identified as ``RC'' (required for 
compliance) in the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-57A2360, Revision 1, dated February 9, 2022, described 
previously.
    For information on the procedures and compliance times, see this 
service information at www.regulations.gov by searching for and 
locating Docket No. FAA-2022-1054.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 207 airplanes of U.S. registry. The FAA estimates the following 
costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                  Cost on U.S.
             Action                  Labor cost           Parts cost         Cost per product      operators
----------------------------------------------------------------------------------------------------------------
Fuse pin replacement \1\         Up to 46 work-     Up to $15,150.........  Up to $19,060 per  Up to $3,945,420
 (retained actions from AD 2017-  hours x $85 per                            replacement        per replacement
 18-05).                          hour = $3,910                              cycle.             cycle.
                                  per replacement
                                  cycle.
Magnetic particle inspection     Up to 48 work-     $0....................  Up to $4,080 per   Up to $844,560
 \1\ (retained actions from AD    hours x $85 per                            inspection cycle.  per inspection
 2017-18-05).                     hour = $4,080                                                 cycle.
                                  per inspection
                                  cycle.
Surface inspection \1\           Up to 10 work-     $0....................  Up to $850 per     Up to $175,950
 (retained actions from AD 2017-  hours x $85 per                            inspection cycle.  per inspection
 18-05).                          hour = $850 per                                               cycle.
                                  inspection cycle.
CRES fuse pin replacement \1\    Up to 46 work-     $9,007................  Up to $12,917 per  Up to $2,673,819
 (new proposed action).           hours x $85 per                            replacement        per replacement
                                  hour = $3,910                              cycle.             cycle.
                                  per replacement
                                  cycle.
Steel alloy fuse pin             Up to 46 work-     $9,693................  Up to $13,603 per  Up to $2,815,821
 replacement\1\ (new proposed     hours x $85 per                            replacement        per replacement
 action).                         hour = $3,910                              cycle.             cycle.
                                  per replacement
                                  cycle.
Surface HFEC and UT              Up to 11 work-     $0....................  Up to $935 per     Up to $193,545
 inspections\1\ (new proposed     hours x $85 per                            inspection cycle.  per inspection
 action).                         hour = $935 per                                               cycle.
                                  inspection cycle.
----------------------------------------------------------------------------------------------------------------
\1\ Operators may choose which action they want to use.

    The FAA estimates the following costs to do any necessary 
replacements and inspections that would be required based on the 
results of the proposed inspections. The FAA has no way of determining 
the number of aircraft that might need these replacements and 
inspections:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
CRES fuse pin replacement.....................  46 work-hours x $85 per hour =            $9,007         $12,917
                                                 $3,910.
Steel alloy fuse pin replacement..............  46 work-hours x $85 per hour =             9,693          13,603
                                                 $3,910.
Magnetic particle inspection..................  48 work-hours x $85 per hour =                 0           4,080
                                                 $4,080.
Surface HFEC and UT inspections...............  11 work-hours x $85 per hour =                 0             935
                                                 $935.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, General requirements. 
Under that section, Congress charges the FAA with promoting safe flight 
of civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    The FAA has determined that this proposed AD would not have 
federalism implications under Executive Order 13132. This proposed AD 
would not have a substantial direct effect on the States, on the 
relationship between the national Government and the States, or on the 
distribution of power and responsibilities among the various levels of 
government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Would not affect intrastate aviation in Alaska, and
    (3) Would not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

[[Page 57158]]

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive (AD) 2017-18-05; Amendment 39-19014 
(82 FR 41331, August 31, 2017), and
0
b. Adding the following new AD:

The Boeing Company: Docket No. FAA-2022-1054; Project Identifier AD-
2022-00278-T.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) action by November 3, 2022.

(b) Affected ADs

    This AD replaces AD 2017-18-05; Amendment 39-19014 (82 FR 41331, 
August 31, 2017) (AD 2017-18-05).

(c) Applicability

    This AD applies to all The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 
747-400D, 747-400F, 747SR, 747SP, 747-8F, and 747-8 series 
airplanes, certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by a report of damage found at the lower 
trailing edge panels of the left wing and a broken fuse pin of the 
landing gear beam end fitting, and the determination that repetitive 
ultrasonic testing inspections of the fuse pin for any cracking and 
optional repetitive replacement of certain CRES and steel alloy fuse 
pins is necessary to address the unsafe condition. The FAA is 
issuing this AD to detect and correct cracking in the fuse pin of 
the wing landing gear beam end fitting. A broken fuse pin will not 
support the wing landing gear beam, causing damage to the 
surrounding structure, including flight control cables and hydraulic 
systems, which could result in loss of controllability of the 
airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    Except as specified by paragraph (h) of this AD: At the 
applicable times specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-57A2360, Revision 1, dated 
February 9, 2022, do all applicable actions identified as ``RC'' 
(required for compliance) in, and in accordance with, the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2360, Revision 1, dated February 9, 2022.

(h) Exceptions to Service Information Specifications

    (1) Where the Compliance Time columns of the tables in the 
``Compliance'' paragraph of Boeing Alert Service Bulletin 747-
57A2360, Revision 1, dated February 9, 2022, use the phrase ``the 
original issue date of this service bulletin,'' this AD requires 
using the date of October 5, 2017 (the effective date of AD 2017-18-
05).
    (2) Where the Compliance Time columns of the tables in the 
``Compliance'' paragraph of Boeing Alert Service Bulletin 747-
57A2360, Revision 1, dated February 9, 2022, use the phrase ``the 
Revision 1 date of this service bulletin,'' this AD requires using 
``the effective date of this AD.''

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle ACO Branch, FAA, has the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request 
to your principal inspector or responsible Flight Standards Office, 
as appropriate. If sending information directly to the manager of 
the certification office, send it to the attention of the person 
identified in paragraph (j)(1) of this AD. Information may be 
emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the responsible Flight Standards Office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by The Boeing Company Organization Designation 
Authorization (ODA) that has been authorized by the Manager, Seattle 
ACO Branch, FAA, to make those findings. To be approved, the repair 
method, modification deviation, or alteration deviation must meet 
the certification basis of the airplane, and the approval must 
specifically refer to this AD.
    (4) Except as specified by paragraph (h) of this AD: For service 
information that contains steps that are labeled as Required for 
Compliance (RC), the provisions of paragraphs (i)(4)(i) and (ii) of 
this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. If a step or substep is labeled ``RC Exempt,'' then the 
RC requirement is removed from that step or substep. An AMOC is 
required for any deviations to RC steps, including substeps and 
identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(j) Related Information

    (1) For more information about this AD, contact Stefanie Roesli, 
Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 
South 216th St., Des Moines, WA 98198; phone and fax: 206-231-3964; 
email: [email protected].
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Contractual & Data Services 
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; internet www.myboeingfleet.com. You 
may view this referenced service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 2200 
South 216th St., Des Moines, WA. For information on the availability 
of this material at the FAA, call 206-231-3195.

    Issued on August 12, 2022.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2022-19960 Filed 9-16-22; 8:45 am]
BILLING CODE 4910-13-P


