Airworthiness Directives; Gulfstream Aerospace Corporation Airplanes, 48500-48504 [2024-12581]

Download as PDF 48500 Federal Register / Vol. 89, No. 111 / Friday, June 7, 2024 / Rules and Regulations ddrumheller on DSK120RN23PROD with RULES1 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for Section 504 grants to $25,000,000 (in comparison to $32,000,000 in the Consolidated Appropriations Act, 2023) and rescinded $28,000,000 of the unobligated balances that carried over from prior year appropriations.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lower program level and no available carryover funds, the waiver to the age requirement is no longer supportable and is rescinded.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 FEMA website at: https:// www.fema.gov/disaster/declarations. programs are prohibited from discriminating based on race, color, national origin, religion, sex, gender identity (including gender expression), sexual orientation, disability, age, marital status, family/parental status, income derived from a public assistance program, political beliefs, or reprisal or retaliation for prior civil rights activity, in any program or activity conducted or funded by USDA (not all bases apply to all programs). Remedies and complaint filing deadlines vary by program or incident. Program information may be made available in languages other than English. Persons with disabilities who require alternative means of communication to obtain program information (e.g., Braille, large print, audiotape, American Sign Language) should contact the responsible Mission Area, agency, staff office; or the 711 Federal Relay Service. To file a program discrimination complaint, a complainant should complete a Form AD–3027, USDA Program Discrimination Complaint Form, which can be obtained online at https:// www.usda.gov/sites/default/files/ documents/ad-3027.pdf, from any USDA office, by calling (866) 632–9992, or by writing a letter addressed to USDA. The letter must contain the complainant’s name, address, telephone number, and a written description of the alleged discriminatory action in sufficient detail to inform the Assistant Secretary for Civil Rights about the nature and date of an alleged civil rights violation. The completed AD–3027 form or letter must be submitted to USDA by: (1) Mail: U.S. Department of Agriculture, Office of the Assistant Secretary for Civil Rights, 1400 Independence Avenue SW, Washington, DC 20250–9410; or (2) Fax: (833) 256–1665 or (202) 690– 7442; or (3) Email: program.intake@usda.gov. USDA is an equal opportunity provider, employer, and lender. Joaquin Altoro, Administrator, Rural Housing Service. [FR Doc. 2024–12559 Filed 6–6–24; 8:45 am] BILLING CODE 3410–XV–P Non-Discrimination Statement In accordance with Federal civil rights laws and USDA civil rights regulations and policies, the USDA, its mission areas, agencies, staff offices, employees, and institutions participating in or administering USDA VerDate Sep<11>2014 15:54 Jun 06, 2024 Jkt 262001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 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: E:\FR\FM\07JNR1.SGM 07JNR1 Federal Register / Vol. 89, No. 111 / Friday, June 7, 2024 / Rules and Regulations 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. ddrumheller on DSK120RN23PROD with RULES1 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, VerDate Sep<11>2014 15:54 Jun 06, 2024 Jkt 262001 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- PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 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 E:\FR\FM\07JNR1.SGM 07JNR1 48502 Federal Register / Vol. 89, No. 111 / Friday, June 7, 2024 / Rules and Regulations 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: ddrumheller on DSK120RN23PROD with RULES1 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. VerDate Sep<11>2014 15:54 Jun 06, 2024 Jkt 262001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\07JNR1.SGM 07JNR1 Federal Register / Vol. 89, No. 111 / Friday, June 7, 2024 / Rules and Regulations 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. ddrumheller on DSK120RN23PROD with RULES1 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. VerDate Sep<11>2014 15:54 Jun 06, 2024 Jkt 262001 § 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; PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 48503 (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 E:\FR\FM\07JNR1.SGM 07JNR1 48504 Federal Register / Vol. 89, No. 111 / Friday, June 7, 2024 / Rules and Regulations 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


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