Airworthiness Directives; Gulfstream Aerospace Corporation Airplanes, 48500-48504 [2024-12581]
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Federal Register / Vol. 89, No. 111 / Friday, June 7, 2024 / Rules and Regulations
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Register (88 FR 45809). The purpose of
the notice was to waive four regulatory
requirements for the Section 504 Home
Repair Loans and Grants in a
Presidentially Declared Disaster Areas
(PDDAs) pilot program. The Agency’s
intention was to evaluate the existing
regulations and remove regulatory
barriers to assist eligible applicants in
PDDAs to improve the program usage
for very low-income homeowners that
are seeking to repair their damaged
homes that are in PDDAs. The Agency
also published a correction notice dated
September 6, 2023 (88 FR 60883). In the
September 6, 2023, notice, the Agency
stated that the pilot was subject to the
availability of funds.
As stated in the original notice and
the correction notice, the Agency has
continued to monitor the effectiveness
of the pilot and the availability of funds.
The Agency has now determined that
there are not sufficient funds available
for this program to keep all the waivers
under the pilot in place. The
Consolidated Appropriations Act, 2024
reduced the program level for Section
504 grants to $25,000,000 (in
comparison to $32,000,000 in the
Consolidated Appropriations Act, 2023)
and rescinded $28,000,000 of the
unobligated balances that carried over
from prior year appropriations. With the
lower program level and no available
carryover funds, the waiver to the age
requirement is no longer supportable
and is rescinded. With the rescission of
this one waiver, all applicants for the
Section 504 Home Repair Grant Program
must be 62 years of age or older at the
time of application, according to 7 CFR
3550.103(b). Complete applications
received prior to the date of this notice
can be processed with the age
requirement waiver.
The remaining regulatory waivers
established for the Section 504 PDDAs
pilot program will remain in place and
are anticipated to continue until July 18,
2025. This pilot remains subject to the
availability of funds.
Eligibility Requirements
Eligible participants in the Section
504 program must abide by the statutory
requirements as set forth in 7 CFR part
3550. Eligible PDDAs (individual and
public assistance) can be found on the
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(3) Email: program.intake@usda.gov.
USDA is an equal opportunity
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Joaquin Altoro,
Administrator, Rural Housing Service.
[FR Doc. 2024–12559 Filed 6–6–24; 8:45 am]
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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
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
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 walkaround 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.
SUMMARY:
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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 pubs@
gulfstream.com; 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: 9-ASO-ATLACO-ADs@
faa.gov.
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.
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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,
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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: 9ASO-ATLACO-ADs@faa.gov. 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 postproduction 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-
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48501
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 inservice 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/postcertificate 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 nonconforming 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 nonconforming 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
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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
Action
Labor cost
Inspection of engine mount installation hardware
AMM revision .........................................................
10 work-hours × $85 per hour = $850 ....
1 work-hour × $85 per hour = $85 ..........
The FAA estimates the following
costs to do any necessary repairs that
Cost per
product
Parts cost
would be required based on the results
of the inspection. The FAA has no way
$0
0
Cost on U.S.
operators
$850
85
$209,950
20,995
of determining the number of aircraft
that might need this repair:
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ON-CONDITION COSTS
Action
Labor cost
Parts cost
Engine mount hardware repair ...............................
1 work-hour × $85 per hour = $85 .........................
Up to $4,651 * ....
Cost per engine
Up to $4,736.
* 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.
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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.
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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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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§ 39.13
[Amended]
2. The FAA amends § 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;
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(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 nonconforming engine mount installation. Nonconforming 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
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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.
ddrumheller on DSK120RN23PROD with RULES1
(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: 9-ASO-ATLACO-ADs@faa.gov.
(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.
VerDate Sep<11>2014
15:54 Jun 06, 2024
Jkt 262001
(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 pubs@gulfstream.com;
website gulfstream.com/en/customersupport.
(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 fr.inspection@nara.gov.
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
Authority for This Rulemaking
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2023–2483; Airspace
Docket No. 23–AGL–24]
RIN 2120–AA66
Amendment of VOR Federal Airways
V–48, V–52, V–216, and V–434, and
Revocation of VOR Federal Airway V–
206 in the Vicinity of Ottumwa, IA
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
This action amends Very High
Frequency Omnidirectional Range
SUMMARY:
PO 00000
Frm 00010
Fmt 4700
(VOR) Federal Airways V–48, V–52, V–
216, and V–434, and revokes VOR
Federal Airway V–206. The FAA is
taking this action due to the planned
decommissioning of the VOR portion of
the Ottumwa, IA (OTM), VOR/Distance
Measuring Equipment (VOR/DME)
navigational aid (NAVAID). The
Ottumwa VOR is being decommissioned
in support of the FAA’s VOR Minimum
Operational Network (MON) program.
DATES: Effective date 0901 UTC,
September 5, 2024. The Director of the
Federal Register approves this
incorporation by reference action under
1 CFR part 51, subject to the annual
revision of FAA Order JO 7400.11 and
publication of conforming amendments.
ADDRESSES: A copy of the Notice of
Proposed Rulemaking (NPRM), all
comments received, this final rule, and
all background material may be viewed
online at www.regulations.gov using the
FAA Docket number. Electronic
retrieval help and guidelines are
available on the website. It is available
24 hours each day, 365 days each year.
FAA Order JO 7400.11H, Airspace
Designations and Reporting Points, and
subsequent amendments can be viewed
online at www.faa.gov/air_traffic/
publications/. You may also contact the
Rules and Regulations Group, Office of
Policy, Federal Aviation
Administration, 800 Independence
Avenue SW, Washington, DC 20591;
telephone: (202) 267–8783.
FOR FURTHER INFORMATION CONTACT:
Colby Abbott, Rules and Regulations
Group, Office of Policy, Federal
Aviation Administration, 800
Independence Avenue SW, Washington,
DC 20591; telephone: (202) 267–8783.
SUPPLEMENTARY INFORMATION:
Sfmt 4700
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the United States Code.
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. This rulemaking is
promulgated under the authority
described in Subtitle VII, Part A,
Subpart I, Section 40103. Under that
section, the FAA is charged with
prescribing regulations to assign the use
of the airspace necessary to ensure the
safety of aircraft and the efficient use of
airspace. This regulation is within the
scope of that authority as it modifies the
Air Traffic Service (ATS) route structure
as necessary to preserve the safe and
efficient flow of air traffic within the
National Airspace System.
E:\FR\FM\07JNR1.SGM
07JNR1
Agencies
[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]
=======================================================================
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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