Airworthiness Directives; The Boeing Company Airplanes, 16654-16659 [2022-05691]

Download as PDF 16654 Federal Register / Vol. 87, No. 57 / Thursday, March 24, 2022 / Proposed Rules List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ Bell Textron Canada Limited (Type Certificate Previously Held by Bell Helicopter Textron Canada Limited): Docket No. FAA–2022–0286; Project Identifier AD–2021–01081–R. (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) by May 9, 2022. (b) Affected ADs None. (c) Applicability This AD applies to Bell Textron Canada Limited (type certificate previously held by Bell Helicopter Textron Canada Limited) Model 206L, 206L–1, 206L–3, and 206L–4 helicopters, certificated in any category, with main rotor (M/R) blade part number (P/N) 20633000–101 with serial number A007, A008, A009, or A012 through A104 inclusive installed under Supplemental Type Certificate SR02684LA. (d) Subject Joint Aircraft System Component (JASC) Code: 6210, Main Rotor Blades. khammond on DSKJM1Z7X2PROD with PROPOSALS (e) Unsafe Condition This AD was prompted by reports of delamination of M/R blades. The FAA is issuing this AD to address delamination of an M/R blade initiating in the 90° plies at the lower inboard end of the weight pocket receptacle. The unsafe condition, if not addressed, could result in reduced structural integrity of the M/R blade, excessive vibration, and subsequent loss of control of the helicopter. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Accomplish the actions required by paragraph (g)(2) of this AD at the following compliance time, whichever occurs later: (i) Before the M/R blade accumulates 400 total hours time-in-service (TIS) or 2,400 VerDate Sep<11>2014 16:36 Mar 23, 2022 Jkt 256001 engine starts since initial installation on any helicopter, whichever occurs first; or (ii) Within 100 hours TIS after the effective date of this AD. (2) Remove each M/R blade from the helicopter, place it on a flat, stable surface, and accomplish the following: (i) Use a permanent marker to draw rectangular inspection ‘‘Zone 1’’ on the upper surface of the M/R blade at M/R blade stations 186.0 and 191.0, beginning 1.1 inches from the leading edge of the M/R blade to 4.9 inches from the leading edge of the M/R blade. Draw lines from the inboard end to the outboard end to connect each end at 1.1 inches and 4.9 inches. Draw parallel lines from the inboard end of the inspection zone to the outboard end of the inspection zone, with the lines spaced 0.50 inch apart. Note 1 to paragraph (g)(2)(i): This note applies to paragraphs (g)(2)(i) and (ii) of this AD. Figure 4 of Van Horn Aviation, L.L.C., Service Bulletin Notice No. 33000–4R3, dated November 8, 2021 (SB 33000–4R3) depicts ‘‘Zone 1’’ and ‘‘Zone 2.’’ (ii) Use a permanent marker to draw rectangular inspection ‘‘Zone 2’’ on the lower surface of the M/R blade at M/R blade stations 186.0 and 191.0, beginning from the forward edge of the weight receptacle pocket and extending 1 inch in the direction towards the leading edge of the M/R blade. Draw lines from the inboard end to the outboard end to connect each end at the weight receptacle pocket and 1 inch forward of the weight receptacle pocket. Draw parallel lines from the inboard end of the inspection zone to the outboard end of the inspection zone, with the lines spaced 0.50 inch apart. (iii) Using composite tap hammer Abaris Training Tap Hammer P/N ABATH, HeatCon Tap Hammer P/N HCS1104–01, Brown Tool Composite Tap Hammer P/N BAT–CTH8, or MATCO Tools Composite Tap Hammer P/N T4BAT–CTH8, tap inspect the areas within ‘‘Zone 1’’ and ‘‘Zone 2’’ for any delamination by following Tap Inspect Balance Receptacle, paragraph A.(4) of SB 33000–4R3. Where SB 33000–4R3 specifies to mark the location where the delamination starts, use a permanent marker. (iv) If there are any marks where the delamination starts, connect the marks indicating the delamination location and measure the length at the farthest point from the inboard end of the inspection area. (v) If there is any delamination in the lower surface inspection zone (‘‘Zone 2’’) that is 6.0 or more inches in length or if there is any delamination in the upper surface inspection zone (‘‘Zone 1’’), before further flight, remove the M/R blade from service. (3) Thereafter repeat the actions required by paragraph (g)(2) of this AD at intervals not to exceed 400 hours TIS or 2,400 engine starts, whichever occurs first. (4) If there is any delamination, within 30 days after accomplishing the actions required by paragraphs (g)(1) or (3) of this AD, report each delamination size and location, and the total hours TIS and total engine starts since initial installation of the M/R blade, to Mr. Dean Rosenlof, Van Horn Aviation, L.L.C., 1510 West Drake Drive, Tempe, AZ 85283, or by email to info@vanhornaviation.com. PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles ACO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (i)(1) of this AD. Information may be emailed to: 9ANM-LAACO-AMOC-REQUESTS@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (i) Related Information (1) For more information about this AD, contact Peter Jarzomb, Aerospace Engineer, Airframe Section, Los Angeles ACO Branch, Compliance & Airworthiness Division, FAA, 3960 Paramount Blvd., Lakewood, CA 90712; telephone (562) 627–5234; email peter.jarzomb@faa.gov. (2) For service information identified in this AD, contact Van Horn Aviation, L.L.C., ATTN: Dean Rosenlof, 1510 West Drake Drive, Tempe, AZ 85283; telephone (480) 483–4202; email dean@vanhornaviation.com. You may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222–5110. Issued on March 15, 2022. Derek Morgan, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022–05874 Filed 3–23–22; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2022–0148; Project Identifier AD–2021–00922–T] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to supersede Airworthiness Directive (AD) 2015–12–03, which applies to certain The Boeing Company Model 777–200, –200LR, –300, and –300ER series airplanes. AD 2015–12–03 requires repetitive freeplay inspections and lubrication of the right and left SUMMARY: E:\FR\FM\24MRP1.SGM 24MRP1 Federal Register / Vol. 87, No. 57 / Thursday, March 24, 2022 / Proposed Rules elevators, rudder, and rudder tab, and related investigative and corrective actions if necessary. Since the FAA issued AD 2015–12–03, engineering testing revealed that the force being applied to the elevator to detect excessive freeplay was insufficient. This proposed AD would continue to require certain actions in AD 2015–12–03 for certain airplanes, and would require revising the existing maintenance or inspection program, as applicable, for certain other airplanes, to incorporate a revised or new elevator freeplay maintenance procedure, as applicable. This proposed AD would also add airplanes to the applicability. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by May 9, 2022. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; internet https:// www.myboeingfleet.com. You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available at https:// www.regulations.gov by searching for and locating Docket No. FAA–2022– 0148. khammond on DSKJM1Z7X2PROD with PROPOSALS Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2022–0148; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, any comments received, and other information. The street address for Docket Operations is listed above. VerDate Sep<11>2014 16:36 Mar 23, 2022 Jkt 256001 Luis Cortez-Muniz, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: (206) 231–3958; email: Luis.A.CortezMuniz@faa.gov. SUPPLEMENTARY INFORMATION: FOR FURTHER INFORMATION CONTACT: Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2022–0148; Project Identifier AD– 2021–00922–T’’ at the beginning of your comments. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend the proposal because of those comments. Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to https:// www.regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this proposed AD. Confidential Business Information CBI is commercial or financial information that is both customarily and actually treated as private by its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this NPRM contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this NPRM, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as ‘‘PROPIN.’’ The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this NPRM. Submissions containing CBI should be sent to Luis Cortez-Muniz, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: (206) 231–3958; email: Luis.A.Cortez-Muniz@faa.gov. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 16655 Background The FAA issued AD 2015–12–03, Amendment 39–18176 (80 FR 34252, June 16, 2015) (AD 2015–12–03), for certain The Boeing Company Model 777–200, –200LR, –300, and –300ER series airplanes. AD 2015–12–03 was prompted by the manufacturer’s determination that the procedure for the rudder freeplay inspection available at the time did not properly detect excessive freeplay in the rudder control load loop. AD 2015–12–03 requires repetitive freeplay inspections and lubrication of the right and left elevators, rudder, and rudder tab, and related investigative and corrective actions if necessary. The agency issued AD 2015–12–03 to detect and correct excessive wear in the load loop components of the control surfaces, which could lead to excessive freeplay of the control surfaces, flutter, and consequent loss of control of the airplane. AD 2015–12–03 superseded AD 2007– 13–05, Amendment 39–15109 (72 FR 33856, June 20, 2007). Actions Since AD 2015–12–03 Was Issued Since the FAA issued AD 2015–12– 03, engineering testing revealed that the force being applied to the elevator to detect excessive freeplay was insufficient. The original bypass test setup for the power control unit (PCU), which used a hydraulic depressurization method, was found to be unreliable for putting the adjacent PCU into bypass mode, and a new elevator freeplay maintenance procedure is necessary. Model 777F airplanes were not added to the applicability in AD 2015–12–03 because there was a certification maintenance requirement (CMR) task to accomplish the freeplay inspections for those airplanes; therefore, the FAA has determined that it is necessary for operators to revise the maintenance or inspection program to update the elevator freeplay procedures for Model 777F airplanes. FAA’s Determination The FAA is issuing this NPRM after determining that the unsafe condition described previously is likely to exist or develop on other products of the same type design. Related Service Information Under 1 CFR Part 51 The FAA reviewed Boeing Special Attention Service Bulletin 777–27– 0062, Revision 4, dated July 15, 2021. This service information specifies procedures for changing the elevator E:\FR\FM\24MRP1.SGM 24MRP1 16656 Federal Register / Vol. 87, No. 57 / Thursday, March 24, 2022 / Proposed Rules freeplay instructions by adding changes to the input force, elevator freeplay limit, and PCU bypass test setup. This proposed AD would also require Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014, which the Director of the Federal Register approved for incorporation by reference as of July 21, 2015 (80 FR 34253, June 16, 2015). This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Proposed AD Requirements in This NPRM This proposed AD would retain certain requirements of AD 2015–12–03 and require accomplishing the actions specified in accordance with updated service information, including corrective actions, such as repairs, already described for Model 777–200, –200LR, –300, and –300ER airplanes. This proposed AD would also add Model 777F series airplanes to the applicability. For Model 777F series airplanes, this proposed AD would require revising the existing maintenance or inspection program, as applicable, to incorporate a new elevator freeplay maintenance procedure. For information on the procedures and compliance times, see this service information at https:// www.regulations.gov by searching for and locating Docket No. FAA–2022– 0148. Costs of Compliance The FAA estimates that this AD, if adopted as proposed, would affect 281 airplanes of U.S. registry. The FAA estimates the following costs to comply with this proposed AD: ESTIMATED COSTS Required actions Labor cost Measurement (inspection), elevator. Lubrication, elevator ......... 4 work-hours × $85 per hour = $340 per measurement (inspection) cycle. 17 work-hours × $85 per hour = $1,445 per lubrication cycle. 4 work-hours × $85 per hour = $340 per measurement (inspection) cycle. 7 work-hours × $85 per hour = $595 per lubrication cycle. 3 work-hours × $85 per hour = $255 per measurement (inspection) cycle. 5 work-hours × $85 per hour = $425 per lubrication cycle. Measurement (inspection), rudder. Lubrication, rudder ............ Measurement (inspection), rudder tab. Lubrication, rudder tab ...... The FAA has received no definitive data that would enable the agency to provide cost estimates for the oncondition corrective actions specified in this proposed AD. The FAA has determined that revising the existing maintenance or inspection program takes an average of 90 workhours per operator, although the agency recognizes that this number may vary from operator to operator. Since operators incorporate maintenance or inspection program changes for their affected fleet(s), the FAA has determined that a per-operator estimate is more accurate than a per-airplane estimate. Therefore, the FAA estimates the average total cost per Model 777F operator to be $7,650 (90 work-hours × $85 per work-hour). khammond on DSKJM1Z7X2PROD with PROPOSALS 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 VerDate Sep<11>2014 16:36 Mar 23, 2022 Jkt 256001 Parts cost $0 0 0 0 0 0 Cost per product Cost on U.S. operators (218) $340 per measurement (inspection) cycle. $1,445 per lubrication cycle. $340 per measurement (inspection) cycle. $595 per lubrication cycle $74,120 per measurement (inspection) cycle. $315,010 per lubrication cycle. $74,230 per measurement (inspection) cycle. $129,710 per lubrication cycle. $55,590 per measurement (inspection) cycle. $92,650 per lubrication cycle. $255 per measurement (inspection) cycle. $425 per lubrication cycle 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. List of Subjects in 14 CFR Part 39 Regulatory Findings PART 39—AIRWORTHINESS DIRECTIVES The FAA has determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Would not affect intrastate aviation in Alaska, and (3) Would not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by: ■ a. Removing Airworthiness Directive (AD) 2015–12–03, Amendment 39– 18176 (80 FR 34252, June 16, 2015), and ■ b. Adding the following new AD: ■ The Boeing Company: Docket No. FAA– 2022–0148; Project Identifier AD–2021– 00922–T. (a) Comments Due Date The FAA must receive comments on this airworthiness directive (AD) action by May 9, 2022. E:\FR\FM\24MRP1.SGM 24MRP1 Federal Register / Vol. 87, No. 57 / Thursday, March 24, 2022 / Proposed Rules (b) Affected ADs This AD replaces AD 2015–12–03, Amendment 39–18176 (80 FR 34252, June 16, 2015) (AD 2015–12–03). (c) Applicability This AD applies to The Boeing Company airplanes, certificated in any category, identified in paragraphs (c)(1) and (2) of this AD. (1) All Model 777–200, –200LR, –300, –300ER series airplanes. (2) Model 777F airplanes with an original airworthiness certificate or original export certificate of airworthiness issued on or before the effective date of this AD. (d) Subject Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Unsafe Condition This AD was prompted by the manufacturer’s determination that the procedure for the rudder freeplay inspection available at the time did not properly detect excessive freeplay in the rudder control load loop. This AD was also prompted by engineering testing that revealed that the force being applied to the elevator to detect excessive freeplay was insufficient. The FAA is issuing this AD to address excessive wear in the load loop components of the control surfaces, which could lead to excessive freeplay of the control surfaces, flutter, and consequent loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. khammond on DSKJM1Z7X2PROD with PROPOSALS (g) Retained Repetitive Inspections of Elevators, Rudder, and Rudder Tab, With Revised Service Information This paragraph restates the requirements of paragraph (g) of AD 2015–12–03, with revised service information. For Model 777– 200, –200LR, –300, and –300ER series airplanes: At the applicable times specified in tables 1, 2, and 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014, or Revision 4, dated July 15, 2021, except as provided by paragraph (i)(1) of this AD: Inspect the freeplay of the right and left elevators, rudder, and rudder tab by accomplishing all of the actions specified in Parts 1, 3, and 5 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014, or Revision 4, dated July 15, 2021, except as provided by paragraphs (i)(2) through (4) of this AD. Repeat the inspections VerDate Sep<11>2014 16:36 Mar 23, 2022 Jkt 256001 thereafter at the intervals specified in tables 1, 2, and 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014, or Revision 4, dated July 15, 2021. If, during any inspection required by this paragraph, the freeplay exceeds any applicable measurement specified in Part 1, 3, and 5, as applicable, of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–27– 0062, Revision 2, dated January 27, 2014, or Revision 4, dated July 15, 2021, before further flight, do the applicable corrective actions in accordance with Part 1, 3, and 5 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014, or Revision 4, dated July 15, 2021. After the effective date of this AD use only Boeing Special Attention Service Bulletin 777–27–0062, Revision 4, dated July 15, 2021. (h) Retained Repetitive Lubrication, With Revised Service Information This paragraph restates the requirements of paragraph (h) of AD 2015–12–03, with revised service information. For Model 777– 200, –200LR, –300, –300ER series airplanes: At the applicable times specified in tables 1, 2, and 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014, or Revision 4, dated July 15, 2021, except as provided by paragraph (i)(1) of this AD: Lubricate the elevator components, rudder components, and rudder tab components, by accomplishing all of the actions specified in Parts 2, 4, and 6 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–27– 0062, Revision 2, dated January 27, 2014, or Revision 4, dated July 15, 2021. Repeat the lubrication thereafter at the interval specified in tables 1, 2, and 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014, or Revision 4, dated July 15, 2021. After the effective date of this AD use only Boeing Special Attention Service Bulletin 777–27–0062, Revision 4, dated July 15, 2021. (i) Retained Exceptions to Service Information Specifications, With Revised Service Information This paragraph restates the requirements of paragraph (i) of AD 2015–12–03, with revised service information, for Model 777–200, –200LR, –300, –300ER series airplanes. (1) Where Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014, and Revision 4, dated July 15, 2021, specify a compliance time ‘‘after PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 16657 the original issue date on this service bulletin,’’ this AD requires compliance within the specified compliance time after July 25, 2007 (the effective date of AD 2007– 13–05, Amendment 39–15109 (72 FR 33856, June 20, 2007)). After the effective date of this AD, only Boeing Special Attention Service Bulletin 777–27–0062, Revision 4, dated July 15, 2021, may be used. (2) Where Appendix B, paragraph 1.f., ‘‘Freeplay Inspection,’’ step (8), of Boeing Special Attention Service Bulletin 777–27– 0062, Revision 2, dated January 27, 2014, specifies that the center of the pad must be within 1.0 inch (13 millimeters) of the center line of the rib rivets in the rudder tab, this AD requires that the center of the tab must be within 1.0 inch (25 millimeters) of the center line of the rib rivets in the rudder tab. (3) Where Appendix C, paragraph 1.e., ‘‘Rudder Tab Surface Freeplay—Inspection,’’ step (2) and step (6), of Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014, specify that the placement of the force gage and pad should be within one inch of the centerline line of the middle rudder PCU rib and at 12 +/¥1 inch (305 +/¥72 millimeters) forward of the rudder tab trailing edge, this AD requires placement of the force gage and pad within one inch of the centerline line of the middle rudder PCU rib and at 12 +/¥1 inch (305 +/¥25 millimeters) forward of the rudder tab trailing edge. (4) Where Appendix C, paragraph 1.e., ‘‘Rudder Tab Surface Freeplay—Inspection,’’ step (3), of Boeing Special Attention Service Bulletin 777–27–0062, Revision 2, dated January 27, 2014, specifies to apply a 30 +/ ¥pound (133 +/¥14 newton) force, this AD requires applying a 30 +/¥3 pound force (133 +/¥14 newton) force. (j) New Maintenance or Inspection Program Revision For Model 777F airplanes: Within 30 days after the effective date of this AD, revise the 777F elevator freeplay maintenance procedure in the existing maintenance or inspection program, as applicable, by doing the actions specified in paragraphs (j)(1) through (3) of this AD. (1) Remove the existing hydraulic depressurization PCU test setup procedure step and replace it by incorporating the information specified in figure 1 to paragraph (j) of this AD. (2) Revise the jack test force used to push the elevator up to 225 +/¥10 lb (102.1 +/ ¥4.5 kg). (3) Revise the elevator freeplay dial indicator limit to 0.34 in. (152 mm) or less. E:\FR\FM\24MRP1.SGM 24MRP1 16658 Federal Register / Vol. 87, No. 57 / Thursday, March 24, 2022 / Proposed Rules Figure 1 to paragraph G): Circuit breaker elevator freeplay test setup Do these steps to prepare for the freeplay inspection: NOTE: Each PCU can be inspected in any order, as long as the setup for the inspection is performed per the steps below. a) To inspect the left elevator outboard PCU, do these steps: 1. Open this circuit breaker and install safety tag: Power Supply Assembly Center, M24301 Row Col Number Name b) A 7 CBA7-C ELEV PCU 2. Make sure that the left elevator inboard PCU is in bypass mode To inspect the left elevator inboard PCU, do these steps: 1. Open this circuit breaker and install safety tag: Power Supply Assembly Left, M24101 Row Col Number Name c) A 7 CBA7-L ELEV PCU 2. Make sure that the left elevator outboard PCU is in bypass mode. To inspect the right elevator inboard PCU, do these steps: 1. Open this circuit breaker and install safety tag: Left Power Management Panel, P110 Row Col Number Name K 27 C27609 ELEV PCU RIB (BLK)/ROB(BYP) 2. Make sure that the right elevator outboard PCU is in bypass mode. d) To inspect the right elevator outboard PCU, do these steps: 1. Open this circuit breaker and install safety tag: Power Supply Assembly Right, M24201 Row Col Number Name A 7 CBA7-R ELEV PCU Make sure that the right elevator inboard PCU is in bypass mode. Note 1 to paragraph (j): Refer to AMM task 27–31–09–200–801, dated September 5, 2021, for additional guidance. khammond on DSKJM1Z7X2PROD with PROPOSALS (k) No Alternative Actions or Intervals After the existing maintenance or inspection program has been revised as required by paragraph (j) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (m) of this AD. (l) Credit for Previous Actions This paragraph provides credit for the actions specified in paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 777–27–0062, Revision 3, dated October 9, 2015. (m) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle ACO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your VerDate Sep<11>2014 16:36 Mar 23, 2022 Jkt 256001 principal inspector or responsible Flight Standards Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (n)(1) of this AD. Information may be emailed to: 9ANM-Seattle-ACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by The Boeing Company Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO Branch, FAA, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved previously for the freeplay measurements of the right and left rudder tab required by AD 2015–12–03, are approved as AMOCs for the corresponding provisions of this AD. (5) AMOCs approved previously for the freeplay measurements of the rudder required by AD 2015–12–03, are approved as PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 AMOCs for the corresponding provisions of this AD. (6) AMOCs approved previously for the repetitive lubrications required by AD 2015– 12–03, are approved as AMOCs for the corresponding provisions of this AD. (n) Related Information (1) For more information about this AD, contact Luis Cortez-Muniz, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: (206) 231–3958; email: Luis.A.Cortez-Muniz@ faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. E:\FR\FM\24MRP1.SGM 24MRP1 EP24MR22.059</GPH> 2. Federal Register / Vol. 87, No. 57 / Thursday, March 24, 2022 / Proposed Rules Issued on February 18, 2022. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [Docket No. FAA–2022–0292; Project Identifier AD–2021–01297–E] p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact International Aero Engines, LLC, 400 Main Street, East Hartford, CT 06118; phone: (860) 690– 9667; email: help24@pw.utc.com; website: http://fleetcare.prattwhitney. com. You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call (817) 222–5110. RIN 2120–AA64 Examining the AD Docket [FR Doc. 2022–05691 Filed 3–23–22; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Airworthiness Directives; International Aero Engines, LLC Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for certain International Aero Engines, LLC (IAE LLC) PW1122G–JM, PW1124G1– JM, PW1124G–JM, PW1127G1–JM, PW1127GA–JM, PW1127G–JM, PW1129G–JM, PW1130G–JM, PW1133GA–JM, and PW1133G–JM model turbofan engines. This proposed AD was prompted by an analysis of an event involving an International Aero Engines AG (IAE AG) V2533–A5 model turbofan engine, which experienced an uncontained failure of a high-pressure turbine (HPT) 1st-stage disk that resulted in high-energy debris penetrating the engine cowling. This proposed AD would require performance of an ultrasonic inspection (USI) of the HPT 1st-stage disk and HPT 2nd-stage disk and, depending on the results of the inspections, replacement of the HPT 1st-stage disk or HPT 2ndstage disk. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by May 9, 2022. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 khammond on DSKJM1Z7X2PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 16:36 Mar 23, 2022 Jkt 256001 You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2022–0292; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, any comments received, and other information. The street address for Docket Operations is listed above. FOR FURTHER INFORMATION CONTACT: Mark Taylor, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238–7229; email: Mark.Taylor@ faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2022–0292; Project Identifier AD– 2021–01297–E’’ at the beginning of your comments. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend this proposal because of those comments. Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to https:// www.regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this NPRM. 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 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 16659 (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this NPRM contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this NPRM, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as ‘‘PROPIN.’’ The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this NPRM. Submissions containing CBI should be sent to Mark Taylor, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803. Any commentary that the FAA receives which is not specifically designated as CBI will be placed in the public docket for this rulemaking. Background On March 18, 2020, an Airbus Model A321–231 airplane, powered by IAE AG V2533–A5 model turbofan engines, experienced an uncontained HPT 1ststage disk failure that resulted in highenergy debris penetrating the engine cowling. Based on a preliminary analysis of this event, on March 21, 2020, the FAA issued Emergency AD 2020–07–51 (followed by publication in the Federal Register on April 13, 2020, as a Final Rule, Request for Comments (85 FR 20402)), which requires the removal from service of certain HPT 1ststage disks installed on IAE AG V2522– A5, V2524–A5, V2525–D5, V2527–A5, V2527E–A5, V2527M–A5, V2528–D5, V2530–A5, and V2533–A5 model turbofan engines. Based on the root cause analysis performed since that March 2020 event, Pratt & Whitney (PW) identified a different population of HPT 1st-stage disks and HPT 2nd-stage disks that are subject to the same unsafe condition identified in AD 2020–07–51. In response, the FAA issued AD 2021–19– 10 on September 10, 2021 (86 FR 50610), which requires the removal from service of certain HPT 1st-stage disks and HPT 2nd-stage disks installed on IAE LLC PW1122G–JM, PW1124G1– JM, PW1124G–JM, PW1127G1–JM, PW1127GA–JM, PW1127G–JM, PW1129G–JM, PW1130G–JM, PW1133GA–JM, and PW1133G–JM model turbofan engines. Since the FAA issued AD 2021–19– 10, PW identified another subpopulation of HPT 1st-stage disks and HPT 2nd-stage disks that require inspection and possible removal from service. Included in this additional subpopulation of HPT 1st-stage disks E:\FR\FM\24MRP1.SGM 24MRP1

Agencies

[Federal Register Volume 87, Number 57 (Thursday, March 24, 2022)]
[Proposed Rules]
[Pages 16654-16659]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-05691]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-0148; Project Identifier AD-2021-00922-T]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2015-12-03, which applies to certain The Boeing Company Model 777-200, 
-200LR, -300, and -300ER series airplanes. AD 2015-12-03 requires 
repetitive freeplay inspections and lubrication of the right and left

[[Page 16655]]

elevators, rudder, and rudder tab, and related investigative and 
corrective actions if necessary. Since the FAA issued AD 2015-12-03, 
engineering testing revealed that the force being applied to the 
elevator to detect excessive freeplay was insufficient. This proposed 
AD would continue to require certain actions in AD 2015-12-03 for 
certain airplanes, and would require revising the existing maintenance 
or inspection program, as applicable, for certain other airplanes, to 
incorporate a revised or new elevator freeplay maintenance procedure, 
as applicable. This proposed AD would also add airplanes to the 
applicability. The FAA is proposing this AD to address the unsafe 
condition on these products.

DATES: The FAA must receive comments on this proposed AD by May 9, 
2022.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Boeing 
Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; 
telephone 562-797-1717; internet https://www.myboeingfleet.com. You may 
view this service information at the FAA, Airworthiness Products 
Section, Operational Safety Branch, 2200 South 216th St., Des Moines, 
WA. For information on the availability of this material at the FAA, 
call 206-231-3195. It is also available at https://www.regulations.gov 
by searching for and locating Docket No. FAA-2022-0148.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2022-0148; or in person at 
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The AD docket contains this NPRM, any comments 
received, and other information. The street address for Docket 
Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Luis Cortez-Muniz, Aerospace Engineer, 
Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des 
Moines, WA 98198; phone and fax: (206) 231-3958; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2022-0148; Project Identifier 
AD-2021-00922-T'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
the proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this proposed AD.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this NPRM, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this NPRM. Submissions containing CBI should be sent to Luis 
Cortez-Muniz, Aerospace Engineer, Airframe Section, FAA, Seattle ACO 
Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 
(206) 231-3958; email: [email protected]. Any commentary that 
the FAA receives which is not specifically designated as CBI will be 
placed in the public docket for this rulemaking.

Background

    The FAA issued AD 2015-12-03, Amendment 39-18176 (80 FR 34252, June 
16, 2015) (AD 2015-12-03), for certain The Boeing Company Model 777-
200, -200LR, -300, and -300ER series airplanes. AD 2015-12-03 was 
prompted by the manufacturer's determination that the procedure for the 
rudder freeplay inspection available at the time did not properly 
detect excessive freeplay in the rudder control load loop. AD 2015-12-
03 requires repetitive freeplay inspections and lubrication of the 
right and left elevators, rudder, and rudder tab, and related 
investigative and corrective actions if necessary. The agency issued AD 
2015-12-03 to detect and correct excessive wear in the load loop 
components of the control surfaces, which could lead to excessive 
freeplay of the control surfaces, flutter, and consequent loss of 
control of the airplane.
    AD 2015-12-03 superseded AD 2007-13-05, Amendment 39-15109 (72 FR 
33856, June 20, 2007).

Actions Since AD 2015-12-03 Was Issued

    Since the FAA issued AD 2015-12-03, engineering testing revealed 
that the force being applied to the elevator to detect excessive 
freeplay was insufficient. The original bypass test setup for the power 
control unit (PCU), which used a hydraulic depressurization method, was 
found to be unreliable for putting the adjacent PCU into bypass mode, 
and a new elevator freeplay maintenance procedure is necessary. Model 
777F airplanes were not added to the applicability in AD 2015-12-03 
because there was a certification maintenance requirement (CMR) task to 
accomplish the freeplay inspections for those airplanes; therefore, the 
FAA has determined that it is necessary for operators to revise the 
maintenance or inspection program to update the elevator freeplay 
procedures for Model 777F airplanes.

FAA's Determination

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

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Boeing Special Attention Service Bulletin 777-27-
0062, Revision 4, dated July 15, 2021. This service information 
specifies procedures for changing the elevator

[[Page 16656]]

freeplay instructions by adding changes to the input force, elevator 
freeplay limit, and PCU bypass test setup.
    This proposed AD would also require Boeing Special Attention 
Service Bulletin 777-27-0062, Revision 2, dated January 27, 2014, which 
the Director of the Federal Register approved for incorporation by 
reference as of July 21, 2015 (80 FR 34253, June 16, 2015).
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Proposed AD Requirements in This NPRM

    This proposed AD would retain certain requirements of AD 2015-12-03 
and require accomplishing the actions specified in accordance with 
updated service information, including corrective actions, such as 
repairs, already described for Model 777-200, -200LR, -300, and -300ER 
airplanes. This proposed AD would also add Model 777F series airplanes 
to the applicability. For Model 777F series airplanes, this proposed AD 
would require revising the existing maintenance or inspection program, 
as applicable, to incorporate a new elevator freeplay maintenance 
procedure. For information on the procedures and compliance times, see 
this service information at https://www.regulations.gov by searching 
for and locating Docket No. FAA-2022-0148.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 281 airplanes of U.S. registry. The FAA estimates the following 
costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
         Required actions               Labor cost        Parts cost      Cost per product     operators (218)
----------------------------------------------------------------------------------------------------------------
Measurement (inspection),          4 work-hours x $85               $0  $340 per             $74,120 per
 elevator.                          per hour = $340                      measurement          measurement
                                    per measurement                      (inspection) cycle.  (inspection)
                                    (inspection) cycle.                                       cycle.
Lubrication, elevator............  17 work-hours x $85               0  $1,445 per           $315,010 per
                                    per hour = $1,445                    lubrication cycle.   lubrication cycle.
                                    per lubrication
                                    cycle.
Measurement (inspection), rudder.  4 work-hours x $85                0  $340 per             $74,230 per
                                    per hour = $340                      measurement          measurement
                                    per measurement                      (inspection) cycle.  (inspection)
                                    (inspection) cycle.                                       cycle.
Lubrication, rudder..............  7 work-hours x $85                0  $595 per             $129,710 per
                                    per hour = $595                      lubrication cycle.   lubrication cycle.
                                    per lubrication
                                    cycle.
Measurement (inspection), rudder   3 work-hours x $85                0  $255 per             $55,590 per
 tab.                               per hour = $255                      measurement          measurement
                                    per measurement                      (inspection) cycle.  (inspection)
                                    (inspection) cycle.                                       cycle.
Lubrication, rudder tab..........  5 work-hours x $85                0  $425 per             $92,650 per
                                    per hour = $425                      lubrication cycle.   lubrication cycle.
                                    per lubrication
                                    cycle.
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data that would enable the 
agency to provide cost estimates for the on-condition corrective 
actions specified in this proposed AD.
    The FAA has determined that revising the existing maintenance or 
inspection program takes an average of 90 work-hours per operator, 
although the agency recognizes that this number may vary from operator 
to operator. Since operators incorporate maintenance or inspection 
program changes for their affected fleet(s), the FAA has determined 
that a per-operator estimate is more accurate than a per-airplane 
estimate. Therefore, the FAA estimates the average total cost per Model 
777F operator to be $7,650 (90 work-hours x $85 per work-hour).

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive (AD) 2015-12-03, Amendment 39-18176 
(80 FR 34252, June 16, 2015), and
0
b. Adding the following new AD:

The Boeing Company: Docket No. FAA-2022-0148; Project Identifier AD-
2021-00922-T.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) action by May 9, 2022.

[[Page 16657]]

(b) Affected ADs

    This AD replaces AD 2015-12-03, Amendment 39-18176 (80 FR 34252, 
June 16, 2015) (AD 2015-12-03).

(c) Applicability

    This AD applies to The Boeing Company airplanes, certificated in 
any category, identified in paragraphs (c)(1) and (2) of this AD.
    (1) All Model 777-200, -200LR, -300, -300ER series airplanes.
    (2) Model 777F airplanes with an original airworthiness 
certificate or original export certificate of airworthiness issued 
on or before the effective date of this AD.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
Controls.

(e) Unsafe Condition

    This AD was prompted by the manufacturer's determination that 
the procedure for the rudder freeplay inspection available at the 
time did not properly detect excessive freeplay in the rudder 
control load loop. This AD was also prompted by engineering testing 
that revealed that the force being applied to the elevator to detect 
excessive freeplay was insufficient. The FAA is issuing this AD to 
address excessive wear in the load loop components of the control 
surfaces, which could lead to excessive freeplay of the control 
surfaces, flutter, and consequent loss of control of the airplane.

(f) Compliance

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

(g) Retained Repetitive Inspections of Elevators, Rudder, and Rudder 
Tab, With Revised Service Information

    This paragraph restates the requirements of paragraph (g) of AD 
2015-12-03, with revised service information. For Model 777-200, -
200LR, -300, and -300ER series airplanes: At the applicable times 
specified in tables 1, 2, and 3 of paragraph 1.E., ``Compliance,'' 
of Boeing Special Attention Service Bulletin 777-27-0062, Revision 
2, dated January 27, 2014, or Revision 4, dated July 15, 2021, 
except as provided by paragraph (i)(1) of this AD: Inspect the 
freeplay of the right and left elevators, rudder, and rudder tab by 
accomplishing all of the actions specified in Parts 1, 3, and 5 of 
the Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 777-27-0062, Revision 2, dated January 27, 2014, or 
Revision 4, dated July 15, 2021, except as provided by paragraphs 
(i)(2) through (4) of this AD. Repeat the inspections thereafter at 
the intervals specified in tables 1, 2, and 3 of paragraph 1.E., 
``Compliance,'' of Boeing Special Attention Service Bulletin 777-27-
0062, Revision 2, dated January 27, 2014, or Revision 4, dated July 
15, 2021. If, during any inspection required by this paragraph, the 
freeplay exceeds any applicable measurement specified in Part 1, 3, 
and 5, as applicable, of the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 777-27-0062, Revision 2, dated 
January 27, 2014, or Revision 4, dated July 15, 2021, before further 
flight, do the applicable corrective actions in accordance with Part 
1, 3, and 5 of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 777-27-0062, Revision 2, dated January 
27, 2014, or Revision 4, dated July 15, 2021. After the effective 
date of this AD use only Boeing Special Attention Service Bulletin 
777-27-0062, Revision 4, dated July 15, 2021.

(h) Retained Repetitive Lubrication, With Revised Service Information

    This paragraph restates the requirements of paragraph (h) of AD 
2015-12-03, with revised service information. For Model 777-200, -
200LR, -300, -300ER series airplanes: At the applicable times 
specified in tables 1, 2, and 3 of paragraph 1.E., ``Compliance,'' 
of Boeing Special Attention Service Bulletin 777-27-0062, Revision 
2, dated January 27, 2014, or Revision 4, dated July 15, 2021, 
except as provided by paragraph (i)(1) of this AD: Lubricate the 
elevator components, rudder components, and rudder tab components, 
by accomplishing all of the actions specified in Parts 2, 4, and 6 
of the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 777-27-0062, Revision 2, dated January 27, 2014, or 
Revision 4, dated July 15, 2021. Repeat the lubrication thereafter 
at the interval specified in tables 1, 2, and 3 of paragraph 1.E., 
``Compliance,'' of Boeing Special Attention Service Bulletin 777-27-
0062, Revision 2, dated January 27, 2014, or Revision 4, dated July 
15, 2021. After the effective date of this AD use only Boeing 
Special Attention Service Bulletin 777-27-0062, Revision 4, dated 
July 15, 2021.

(i) Retained Exceptions to Service Information Specifications, With 
Revised Service Information

    This paragraph restates the requirements of paragraph (i) of AD 
2015-12-03, with revised service information, for Model 777-200, -
200LR, -300, -300ER series airplanes.
    (1) Where Boeing Special Attention Service Bulletin 777-27-0062, 
Revision 2, dated January 27, 2014, and Revision 4, dated July 15, 
2021, specify a compliance time ``after the original issue date on 
this service bulletin,'' this AD requires compliance within the 
specified compliance time after July 25, 2007 (the effective date of 
AD 2007-13-05, Amendment 39-15109 (72 FR 33856, June 20, 2007)). 
After the effective date of this AD, only Boeing Special Attention 
Service Bulletin 777-27-0062, Revision 4, dated July 15, 2021, may 
be used.
    (2) Where Appendix B, paragraph 1.f., ``Freeplay Inspection,'' 
step (8), of Boeing Special Attention Service Bulletin 777-27-0062, 
Revision 2, dated January 27, 2014, specifies that the center of the 
pad must be within 1.0 inch (13 millimeters) of the center line of 
the rib rivets in the rudder tab, this AD requires that the center 
of the tab must be within 1.0 inch (25 millimeters) of the center 
line of the rib rivets in the rudder tab.
    (3) Where Appendix C, paragraph 1.e., ``Rudder Tab Surface 
Freeplay--Inspection,'' step (2) and step (6), of Boeing Special 
Attention Service Bulletin 777-27-0062, Revision 2, dated January 
27, 2014, specify that the placement of the force gage and pad 
should be within one inch of the centerline line of the middle 
rudder PCU rib and at 12 +/-1 inch (305 +/-72 millimeters) forward 
of the rudder tab trailing edge, this AD requires placement of the 
force gage and pad within one inch of the centerline line of the 
middle rudder PCU rib and at 12 +/-1 inch (305 +/-25 millimeters) 
forward of the rudder tab trailing edge.
    (4) Where Appendix C, paragraph 1.e., ``Rudder Tab Surface 
Freeplay--Inspection,'' step (3), of Boeing Special Attention 
Service Bulletin 777-27-0062, Revision 2, dated January 27, 2014, 
specifies to apply a 30 +/-pound (133 +/-14 newton) force, this AD 
requires applying a 30 +/-3 pound force (133 +/-14 newton) force.

(j) New Maintenance or Inspection Program Revision

    For Model 777F airplanes: Within 30 days after the effective 
date of this AD, revise the 777F elevator freeplay maintenance 
procedure in the existing maintenance or inspection program, as 
applicable, by doing the actions specified in paragraphs (j)(1) 
through (3) of this AD.
    (1) Remove the existing hydraulic depressurization PCU test 
setup procedure step and replace it by incorporating the information 
specified in figure 1 to paragraph (j) of this AD.
    (2) Revise the jack test force used to push the elevator up to 
225 +/-10 lb (102.1 +/-4.5 kg).
    (3) Revise the elevator freeplay dial indicator limit to 0.34 
in. (152 mm) or less.

[[Page 16658]]

[GRAPHIC] [TIFF OMITTED] TP24MR22.059

    Note 1 to paragraph (j): Refer to AMM task 27-31-09-200-801, 
dated September 5, 2021, for additional guidance.

(k) No Alternative Actions or Intervals

    After the existing maintenance or inspection program has been 
revised as required by paragraph (j) of this AD, no alternative 
actions (e.g., inspections) or intervals may be used unless the 
actions or intervals are approved as an alternative method of 
compliance (AMOC) in accordance with the procedures specified in 
paragraph (m) of this AD.

(l) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraphs (g) and (h) of this AD, if those actions were performed 
before the effective date of this AD using Boeing Special Attention 
Service Bulletin 777-27-0062, Revision 3, dated October 9, 2015.

(m) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle ACO Branch, FAA, has the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request 
to your principal inspector or responsible Flight Standards Office, 
as appropriate. If sending information directly to the manager of 
the certification office, send it to the attention of the person 
identified in paragraph (n)(1) of this AD. Information may be 
emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the responsible Flight Standards Office
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by The Boeing Company Organization Designation 
Authorization (ODA) that has been authorized by the Manager, Seattle 
ACO Branch, FAA, to make those findings. To be approved, the repair 
method, modification deviation, or alteration deviation must meet 
the certification basis of the airplane, and the approval must 
specifically refer to this AD.
    (4) AMOCs approved previously for the freeplay measurements of 
the right and left rudder tab required by AD 2015-12-03, are 
approved as AMOCs for the corresponding provisions of this AD.
    (5) AMOCs approved previously for the freeplay measurements of 
the rudder required by AD 2015-12-03, are approved as AMOCs for the 
corresponding provisions of this AD.
    (6) AMOCs approved previously for the repetitive lubrications 
required by AD 2015-12-03, are approved as AMOCs for the 
corresponding provisions of this AD.

(n) Related Information

    (1) For more information about this AD, contact Luis Cortez-
Muniz, Aerospace Engineer, Airframe Section, FAA, Seattle ACO 
Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 
(206) 231-3958; email: [email protected].
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Contractual & Data Services 
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this referenced service 
information at the FAA, Airworthiness Products Section, Operational 
Safety Branch, 2200 South 216th St., Des Moines, WA. For information 
on the availability of this material at the FAA, call 206-231-3195.


[[Page 16659]]


    Issued on February 18, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2022-05691 Filed 3-23-22; 8:45 am]
BILLING CODE 4910-13-P