[Federal Register Volume 89, Number 111 (Friday, June 7, 2024)]
[Rules and Regulations]
[Pages 48500-48504]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-12581]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-1476; Project Identifier AD-2024-00090-T; 
Amendment 39-22761; AD 2024-10-15]
RIN 2120-AA64


Airworthiness Directives; Gulfstream Aerospace Corporation 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Gulfstream Aerospace Corporation Model GVII-G500 and GVII-G600 
airplanes. This AD was prompted by a report of a failed rear engine 
mount discovered during a preflight walk-around due to visible engine 
misalignment. This AD requires inspecting the left and right engine 
mount points within the pylons and engine nacelles for non-conforming 
hardware installation, repairing the engine mount points if necessary, 
and revising the existing aircraft maintenance manual (AMM) to include 
revised procedures for engine removal and installation. The FAA is 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective June 7, 2024.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 7, 2024.
    The FAA must receive comments on this AD by July 22, 2024.

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 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.
    AD Docket: You may examine the AD docket at regulations.gov by 
searching for and locating Docket No. FAA-2024-1476; or in person at 
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays.

[[Page 48501]]

The AD docket contains this final rule, any comments received, and 
other information. The street address for Docket Operations is listed 
above.
    Material Incorporated by Reference:
     For Gulfstream material, contact Gulfstream Aerospace 
Corporation, Technical Publications Dept., P.O. Box 2206, Savannah, GA 
31402-2206; telephone 800-810-4853; email [email protected]; website 
gulfstream.com/en/customer-support.
     You may view this material 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-2024-1476.

FOR FURTHER INFORMATION CONTACT: Jeffrey Johnson, Aviation Safety 
Engineer, FAA, 1701 Columbia Avenue, College Park, GA 30337; phone: 
404-474-5554; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written data, views, or arguments 
about this final rule. Send your comments to an address listed under 
the ADDRESSES section. Include Docket No. FAA-2024-1476 and Project 
Identifier AD-2024-00090-T at the beginning of your comments. The most 
helpful comments reference a specific portion of the final rule, 
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 this final rule 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 
regulations.gov, including any personal information you provide. The 
agency will also post a report summarizing each substantive verbal 
contact received about this final rule.

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 AD 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 AD, 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 AD. Submissions containing CBI should be sent to Jeffrey 
Johnson, Aviation Safety Engineer, FAA, 1701 Columbia Avenue, College 
Park, GA 30337; phone: 404-474-5554; 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 has received a report indicating that, on January 31, 2024, 
a partially disengaged rear engine mount was discovered on an in-
service Model GVII-G600 airplane. The flight crew noticed a visible 
misalignment in the pylon area adjacent to the thrust reverser during a 
preflight walk-around. The misalignment was caused by the upper, aft 
engine mount fastener migrating out of position in the pylon area.
    Follow-on inspection revealed the hollow pin was the only hardware 
holding the aft strut in place, and migration of the hollow pin out of 
position was imminent, which would have resulted in the disconnection 
of the strut from the airplane. The cause of the upper rear engine 
mount failure was determined to be the secondary locking device (cotter 
pin) not being installed, and the separation of the retaining nut from 
the single strut attachment bolt, resulting in the bolt migrating out 
of position. The bolt and nut were found at the bottom of the pylon, 
and the required cotter pin was not located. It was believed that 
during a post-production engine removal and installation performed in a 
Gulfstream 145 Repair Station, using the AMM, the rear engine mount 
fasteners on the airplane side were loosened to aid in engine 
installation. It is probable that the aft upper strut attachment nut 
was not properly reinstalled, and the required cotter pin was not 
installed after the bolt and nut were installed. It was determined that 
maintenance personnel did not fully comply with the AMM procedures that 
were current at the time and anecdotal evidence that shows the 
maintenance personnel requested assistance from the production engine 
installation personnel to install the engine.
    Gulfstream immediately performed technical evaluations on numerous 
airplanes, discovering other non-conforming engine mount hardware 
installations, but confirmed that none would have resulted in failure 
of the engine mount system. However, some of the non-conformances were 
found on engines installed in production. This indicates quality 
escapes exist in both production engine installation and in-service 
installation using the AMM procedures.
    Additionally, an FAA investigation discovered numerous 
discrepancies in the production engine installation procedures, along 
with similar discrepancies in the AMM procedures for installing engines 
post-delivery/post-certificate of airworthiness. The FAA identified 
missing hardware callouts in the engine attachment instruction text, 
engine attachment hardware not shown in the AMM graphics, and 
inconsistencies in AMM image view labeling that could lead to 
misinterpretation of hardware orientation (left and right mirror image 
inconsistencies).
    Failure of any single engine mount, if not addressed, could result 
in the separation of an engine from the airplane and subsequent loss of 
control of the airplane. The FAA is issuing this AD to address the 
unsafe condition on these products.

FAA's Determination

    The FAA is issuing this AD because the agency determined the unsafe 
condition described previously is likely to exist or develop in other 
products of the same type design.

Related Material Under 1 CFR Part 51

    The FAA reviewed Gulfstream GVII-G500 Customer Bulletin No. 092 and 
Gulfstream GVII-G600 Customer Bulletin No. 063, both Revision A, both 
dated April 9, 2024. This material specifies procedures for performing 
a one-time general visual inspection of the hardware at all engine 
mounts, attach fittings, links, and struts; for non-conforming engine 
mount hardware installations (including mis-oriented bolts, nuts, pins, 
and washers; all required hardware; application of torque; and correct 
hardware safety installations). This material also specifies reporting 
findings of non-conforming hardware to Gulfstream and returning non-
conforming hardware to conforming configuration before further flight.
    The FAA also reviewed the following AMM tasks for Chapter 71--
Powerplant, of Gulfstream Aerospace GVII-G500 AMM, Document Number GAC-
AC-GVII-G500-AMM-0001, Revision 18, dated March 29, 2024; and 
Gulfstream Aerospace GVII-G600 AMM, Document

[[Page 48502]]

Number GAC-AC-GVII-G600-AMM-0001, Revision 14, dated March 29, 2024. 
This material contains the following revised maintenance procedures for 
engine removal and installation:
     71-20-02 Engine Mount Hardware--Removal/Installation, 71-
20 Mounts;
     71-21-03 Engine Forward Link Assemblies--Removal/
Installation, 71-21 Front Mounts;
     71-21-04 Forward Engine Mount Assembly--Removal/
Installation, 71-21 Front Mounts;
     71-22-03 Aft Engine Mount Strut Assembly--Removal/
Installation, 71-22 Rear Mounts;
     71-23-05 Engine Thrust Strut--Removal/Installation, 71-23 
Mounts: Support Links and Accessories; and
     71-23-06 Engine Alignment Strut--Removal/Installation, 71-
23 Mounts: Support Links and Accessories.
    These documents are distinct since they apply to different airplane 
models.
    This material 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.

AD Requirements

    This AD requires accomplishing the actions specified in the 
material described previously, except as discussed under ``Differences 
Between this AD and the Referenced Material'' and except for any 
differences identified as exceptions in the regulatory text of this AD.

Differences Between This AD and the Referenced Material

    The applicability of this AD is not limited to airplanes identified 
in paragraph I.A., Effectivity, of Gulfstream GVII-G500 Customer 
Bulletin No. 092 and Gulfstream GVII-G600 Customer Bulletin No. 063, 
both Revision A, both dated April 9, 2024. The unsafe condition was 
originally thought to be the result of improper maintenance procedures 
during post-production engine removal and installation. Investigations 
subsequent to the issuance of the original Gulfstream customer 
bulletins were unable to definitively tie the unsafe condition to the 
removal/installation work and have determined that the unsafe condition 
could have originated during production. Therefore, this AD includes 
airplanes that both have and have not had engines replaced since 
production.
    This AD requires inspecting the engine mount hardware installations 
for conforming hardware and revising the existing AMM to include 
revised maintenance procedures for engine removal and installation. 
Where Gulfstream GVII-G500 Customer Bulletin No. 092 and Gulfstream 
GVII-G600 Customer Bulletin No. 063, both Revision A, both dated April 
9, 2024, state a compliance time of 12 months from the initial issue 
date of February 15, 2024, this AD requires a compliance time of within 
30 days after the effective date of this AD.

Justification for Immediate Adoption and Determination of the Effective 
Date

    Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 
U.S.C. 551 et seq.) authorizes agencies to dispense with notice and 
comment procedures for rules when the agency, for ``good cause,'' finds 
that those procedures are ``impracticable, unnecessary, or contrary to 
the public interest.'' Under this section, an agency, upon finding good 
cause, may issue a final rule without providing notice and seeking 
comment prior to issuance. Further, section 553(d) of the APA 
authorizes agencies to make rules effective in less than thirty days, 
upon a finding of good cause.
    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies forgoing notice and comment prior to adoption of this rule 
because failure of any single engine mount could result in separation 
of the engine from the airplane. Accordingly, notice and opportunity 
for prior public comment are impracticable and contrary to the public 
interest pursuant to 5 U.S.C. 553(b)(3)(B).
    The compliance time in this AD is shorter than the time necessary 
for the public to comment and for publication of the final rule. In 
addition, the FAA finds that good cause exists pursuant to 5 U.S.C. 
553(d) for making this amendment effective in less than 30 days, for 
the same reasons the FAA found good cause to forgo notice and comment.

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because the FAA has determined 
that it has good cause to adopt this rule without notice and comment, 
RFA analysis is not required.

Costs of Compliance

    The FAA estimates that this AD affects 247 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspection of engine mount              10 work-hours x $85 per               $0            $850        $209,950
 installation hardware.                  hour = $850.
AMM revision..........................  1 work-hour x $85 per                  0              85          20,995
                                         hour = $85.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary repairs 
that would be required based on the results of the inspection. The FAA 
has no way of determining the number of aircraft that might need this 
repair:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
              Action                    Labor cost               Parts cost                Cost per engine
----------------------------------------------------------------------------------------------------------------
Engine mount hardware repair.....  1 work-hour x $85     Up to $4,651 *............  Up to $4,736.
                                    per hour = $85.
----------------------------------------------------------------------------------------------------------------
* Estimate includes two highest-cost hardware locations: thrust strut and link assembly. Although more locations
  are possible, two locations are used in this estimate based on typical fleet findings to date.


[[Page 48503]]

    The FAA has included all known costs in its cost estimate. 
According to the manufacturer, however, some or all of the costs of 
this AD may be covered under warranty, thereby reducing the cost impact 
on affected operators.

 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, and
    (2) Will not affect intrastate aviation in Alaska.

List of Subjects in 14 CFR Part 39

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

The Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2024-10-15 Gulfstream Aerospace Corporation: Amendment 39-22761; 
Docket No. FAA-2024-1476; Project Identifier AD-2024-00090-T.

(a) Effective Date

    This airworthiness directive (AD) is effective June 7, 2024.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Gulfstream Aerospace Corporation airplanes, 
certificated in any category, identified in paragraphs (c)(1) and 
(2) of this AD.
    (1) Model GVII-G500 airplanes, serial numbers (S/Ns) 72001 
through 72140 inclusive.
    (2) Model GVII-G600 airplanes, S/Ns 73001 through 73148 
inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Powerplant.

(e) Unsafe Condition

    This AD was prompted by a report of a failed rear engine mount 
discovered during a preflight walk-around due to visible engine 
misalignment. The FAA is issuing this AD to address failure of any 
single engine mount. The unsafe condition, if not addressed, could 
result in the separation of an engine from the airplane and 
subsequent loss of control of the airplane.

(f) Compliance

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

(g) Inspection of Engine Mount Hardware Installations

    Within 30 days after the effective date of this AD, do all 
applicable actions identified as ``RC'' (required for compliance) 
in, and in accordance with, the Accomplishment Instructions of the 
applicable material specified in paragraphs (g)(1) and (2) of this 
AD.
    (1) Gulfstream GVII-G500 Customer Bulletin No. 092, Revision A, 
dated April 9, 2024.
    (2) Gulfstream GVII-G600 Customer Bulletin No. 063, Revision A, 
dated April 9, 2024.

(h) Revision of Aircraft Maintenance Manual (AMM)

    Within 30 days after the effective date of this AD, revise the 
existing AMM to incorporate the procedures specified in paragraphs 
(h)(1)(i) through (vi) or (h)(2)(i) through (vi) of this AD, as 
applicable.
    (1) Chapter 71--Powerplant, Gulfstream Aerospace GVII-G500 AMM, 
Document Number GAC-AC-GVII-G500-AMM-0001, Revision 18, dated March 
29, 2024:
    (i) 71-20-02 Engine Mount Hardware--Removal/Installation, 71-20 
Mounts;
    (ii) 71-21-03 Engine Forward Link Assemblies--Removal/
Installation, 71-21 Front Mounts;
    (iii) 71-21-04 Forward Engine Mount Assembly--Removal/
Installation, 71-21 Front Mounts;
    (iv) 71-22-03 Aft Engine Mount Strut Assembly--Removal/
Installation, 71-22 Rear Mounts;
    (v) 71-23-05 Engine Thrust Strut--Removal/Installation, 71-23 
Mounts: Support Links and Accessories; and
    (vi) 71-23-06 Engine Alignment Strut--Removal/Installation, 71-
23 Mounts: Support Links and Accessories.
    (2) Chapter 71--Powerplant, Gulfstream Aerospace GVII-G600 AMM, 
Document Number GAC-AC-GVII-G600-AMM-0001, Revision 14, dated March 
29, 2024:
    (i) 71-20-02 Engine Mount Hardware--Removal/Installation, 71-20 
Mounts;
    (ii) 71-21-03 Engine Forward Link Assemblies--Removal/
Installation, 71-21 Front Mounts;
    (iii) 71-21-04 Forward Engine Mount Assembly--Removal/
Installation, 71-21 Front Mounts;
    (iv) 71-22-03 Aft Engine Mount Strut Assembly--Removal/
Installation, 71-22 Rear Mounts;
    (v) 71-23-05 Engine Thrust Strut--Removal/Installation, 71-23 
Mounts: Support Links and Accessories; and
    (vi) 71-23-06 Engine Alignment Strut--Removal/Installation, 71-
23 Mounts: Support Links and Accessories.

(i) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using the material identified in 
paragraphs (i)(1) through (4) of this AD, as applicable.
    (1) Gulfstream GVII-G500 Alert Customer Bulletin No. 001, dated 
February 7, 2024.
    (2) Gulfstream GVII-G500 Customer Bulletin No. 092, dated 
February 15, 2024.
    (3) Gulfstream GVII-G600 Alert Customer Bulletin No. 001, dated 
February 7, 2024.
    (4) Gulfstream GVII-G600 Customer Bulletin No. 063, dated 
February 15, 2024.

(j) Special Flight Permit

    Special flight permits may be issued in accordance with 14 CFR 
21.197 and 21.199 to operate the airplane to a location where the 
inspection required by this AD can be performed, but special flight 
permits may not be issued to operate the airplane after a visual 
inspection has identified any non-conforming engine mount 
installation. Non-conforming engine mount installations must be 
repaired before further flight.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, East Certification 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

[[Page 48504]]

the person identified in paragraph (l)(1) of this AD.
    (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) For service information that contains steps that are labeled 
as Required for Compliance (RC), the provisions of paragraphs 
(k)(3)(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. 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.

(I) Related Information

    (1) For more information about this AD, contact Jeffrey Johnson, 
Aviation Safety Engineer, FAA, 1701 Columbia Avenue, College Park, 
GA 30337; phone: 404-474-5554; email: [email protected].
    (2) Material identified in this AD that is not incorporated by 
reference is available at the address specified in paragraph (m)(3) 
of this AD.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference of the material listed in this paragraph 
under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this material as applicable to do the actions 
required by this AD, unless the AD specifies otherwise.
    (i) Gulfstream GVII-G500 Customer Bulletin No. 092, Revision A, 
dated April 9, 2024.
    (ii) Gulfstream GVII-G600 Customer Bulletin No. 063, Revision A, 
dated April 9, 2024.
    (iii) Chapter 71--Powerplant, Gulfstream Aerospace GVII-G500 
Aircraft Maintenance Manual (AMM), Document Number GAC-AC-GVII-G500-
AMM-0001, Revision 18, dated March 29, 2024:
    Note 1 to the introductory text of paragraph (m)(2)(iii): The 
manufacturer name is located only on the title page of the document.
    (A) 71-20-02 Engine Mount Hardware--Removal/Installation, 71-20 
Mounts;
    (B) 71-21-03 Engine Forward Link Assemblies--Removal/
Installation, 71-21 Front Mounts;
    (C) 71-21-04 Forward Engine Mount Assembly--Removal/
Installation, 71-21 Front Mounts;
    (D) 71-22-03 Aft Engine Mount Strut Assembly--Removal/
Installation, 71-22 Rear Mounts;
    (E) 71-23-05 Engine Thrust Strut--Removal/Installation, 71-23 
Mounts: Support Links and Accessories; and
    (F) 71-23-06 Engine Alignment Strut--Removal/Installation, 71-23 
Mounts: Support Links and Accessories.
    (iv) Chapter 71--Powerplant, Gulfstream Aerospace GVII-G600 AMM, 
Document Number GAC-AC-GVII-G600-AMM-0001, Revision 14, dated March 
29, 2024:
    Note 2 to the introductory text of paragraph (m)(2)(iv): The 
manufacturer name is located only on the title page of the document.
    (A) 71-20-02 Engine Mount Hardware--Removal/Installation, 71-20 
Mounts;
    (B) 71-21-03 Engine Forward Link Assemblies--Removal/
Installation, 71-21 Front Mounts;
    (C) 71-21-04 Forward Engine Mount Assembly--Removal/
Installation, 71-21 Front Mounts;
    (D) 71-22-03 Aft Engine Mount Strut Assembly--Removal/
Installation, 71-22 Rear Mounts;
    (E) 71-23-05 Engine Thrust Strut--Removal/Installation, 71-23 
Mounts: Support Links and Accessories; and
    (F) 71-23-06 Engine Alignment Strut--Removal/Installation, 71-23 
Mounts: Support Links and Accessories.
    (3) For Gulfstream Aerospace material, contact Gulfstream 
Aerospace Corporation, Technical Publications Dept., P.O. Box 2206, 
Savannah, GA 31402-2206; telephone 800-810-4853; email 
[email protected]; website gulfstream.com/en/customer-support.
    (4) You may view this material at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 2200 South 216th St., 
Des Moines, WA. For information on the availability of this material 
at the FAA, call 206-231-3195.
    (5) You may view this material at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].

    Issued on May 17, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2024-12581 Filed 6-5-24; 11:15 am]
BILLING CODE 4910-13-P