[Federal Register Volume 87, Number 245 (Thursday, December 22, 2022)]
[Rules and Regulations]
[Pages 78515-78518]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-27803]


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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; 
Amendment 39-22255; AD 2022-24-15]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2017-18-
05, which applied 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 required 
repetitive replacement or inspection of certain fuse pins, and 
applicable on-condition actions. This AD was prompted by a report of 
damage found at the lower trailing edge panels

[[Page 78516]]

of the left wing and a broken fuse pin of the landing gear beam end 
fitting. This AD was further prompted by the need for new inspections 
for cracking of the fuse pin, and the determination that additional 
airplanes are subject to the unsafe condition. This AD continues to 
require the actions in AD 2017-18-05 and also requires repetitive 
replacement of certain fuse pins, repetitive inspections for cracking 
of the fuse pin, and applicable on-condition actions. This AD also 
revises the applicability by adding airplanes. The FAA is issuing this 
AD to address the unsafe condition on these products.

DATES: This AD is effective January 26, 2023.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 26, 
2023.

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
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 final rule, any comments received, and other 
information. The address for Docket Operations is U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
    Material Incorporated by Reference:
     For service information identified in this final rule, 
contact Boeing Commercial Airplanes, Attention: Contractual & Data 
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 
90740-5600; telephone 562-797-1717; website myboeingfleet.com.
     You may view 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 
regulations.gov under Docket No. FAA-2022-1054.

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

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2017-18-05, Amendment 39-19014 (82 FR 
41331, August 31, 2017) (AD 2017-18-05). AD 2017-18-05 applied to all 
Boeing 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. 
The NPRM published in the Federal Register on September 19, 2022 (87 FR 
57155). The NPRM was prompted by a report of damage at the lower 
trailing edge panels of the left wing and a broken fuse pin of the 
landing gear beam end fitting. The NPRM was further prompted by the 
need for new ultrasonic testing (UT) inspections for cracking of the 
fuse pin, and the determination that additional airplanes are subject 
to the unsafe condition. In the NPRM, the FAA proposed to continue to 
require repetitive replacement, or repetitive magnetic particle or 
surface high frequency eddy current (HFEC) inspections, of certain fuse 
pins, and applicable on-condition actions. The NPRM also proposed the 
option for repetitive replacement of certain corrosion-resistant 
(stainless) steel (CRES) and steel alloy fuse pins at the wing landing 
gear beam end fitting; and repetitive magnetic particle inspections, or 
repetitive HFEC and UT inspections, for cracking of the fuse pin, and 
applicable on-condition actions. The NPRM also proposed to revise the 
applicability by adding Model 747-8F and 747-8 series airplanes.
    The FAA is issuing this AD to address 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.

Discussion of Final Airworthiness Directive

Comments

    The FAA received a comment from Air Line Pilots Association, 
International, who supported the NPRM without change.

Conclusion

    The FAA reviewed the relevant data, considered any comments 
received, and determined that air safety requires adopting this AD as 
proposed. Accordingly, the FAA is issuing this AD to address the unsafe 
condition on these products. Except for minor editorial changes, this 
AD is adopted as proposed in the NPRM. None of the changes will 
increase the economic burden on any operator.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Boeing Alert Service Bulletin 747-57A2360, 
Revision 1, dated February 9, 2022. This service information specifies 
procedures for, depending on airplane configuration, the 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 HFEC and UT inspections, for cracking and corrosion 
of the fuse pin of the wing landing gear beam end fitting, and 
applicable on-condition actions. On-condition actions include 
replacement with steel alloy or CRES fuse pins; and magnetic particle, 
surface HFEC, and UT testing inspections for cracks; and replacement of 
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 ADDRESSES.

Costs of Compliance

    The FAA estimates that this AD affects 207 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                  Cost on U.S.
             Action                  Labor cost            Parts cost        Cost per product      operators
----------------------------------------------------------------------------------------------------------------
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 = Up to                               cycle.             cycle.
                                  $3,910 per
                                  replacement cycle.
Magnetic particle inspection     Up to 48            $0...................  Up to $4,080 per   Up to $844,560
 \1\ (retained actions from AD    work[dash]hours x                          inspection cycle.  per inspection
 2017-18-05).                     $85 per hour = Up                                             cycle.
                                  to $4,080 per
                                  inspection cycle.
Surface inspection \1\           Up to 10            $0...................  Up to $850 per     Up to $175,950
 (retained actions from AD 2017-  work[dash]hours x                          inspection cycle.  per inspection
 18-05).                          $85 per hour = Up                                             cycle.
                                  to $850 per
                                  inspection cycle.

[[Page 78517]]

 
CRES fuse pin replacement \1\    Up to 46            $9,007...............  Up to $12,917 per  Up to $2,673,819
 (new action).                    work[dash]hours x                          replacement        per replacement
                                  $85 per hour = Up                          cycle.             cycle.
                                  to $3,910 per
                                  replacement cycle.
Steel alloy fuse pin             Up to 46            $9,693...............  Up to $13,603 per  Up to $2,815,821
 replacement \1\ (new action).    work[dash]hours x                          replacement        per replacement
                                  $85 per hour = Up                          cycle.             cycle.
                                  to $3,910 per
                                  replacement cycle.
Surface HFEC and UT              Up to 11            $0...................  Up to $935 per     Up to $193,545
 inspections\1\ (new action).     work[dash]hours x                          inspection cycle.  per inspection
                                  $85 per hour = Up                                             cycle.
                                  to $935 per
                                  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 required 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              35
                                                 $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

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

List of Subjects in 14 CFR Part 39

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

The Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by:
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:

2022-24-15 The Boeing Company: Amendment 39-22255; Docket No. FAA-
2022-1054; Project Identifier AD-2022-00278-T.

(a) Effective Date

    This airworthiness directive (AD) is effective January 26, 2023.

(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 cracking and 
optional repetitive replacement of certain corrosion-resistant 
(stainless) steel (CRES) and steel alloy fuse pins are 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

[[Page 78518]]

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) 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

    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: 206-231-3964; email: 
[email protected].

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Alert Service Bulletin 747-57A2360, Revision 1, dated 
February 9, 2022.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Contractual & Data Services 
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; website myboeingfleet.com.
    (4) You may view 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email [email protected], or go to www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on November 18, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2022-27803 Filed 12-21-22; 8:45 am]
BILLING CODE 4910-13-P