83 FR 26383 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 110 (June 7, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 110 (June 7, 2018)
| Page Range | 26383-26387 | |
| FR Document | 2018-12128 |
[Federal Register Volume 83, Number 110 (Thursday, June 7, 2018)] [Proposed Rules] [Pages 26383-26387] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-12128] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0504; Product Identifier 2018-NM-046-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 707 series airplanes and Model 720 and 720B series airplanes. This proposed AD was prompted by a report indicating that a fracture of the midspar fitting resulted in the separation of the inboard strut and engine from the airplane, and a determination that existing inspections are not sufficient for timely detection of cracking. This proposed AD would require repetitive inspections of certain nacelle strut spar and overwing fittings, and diagonal braces and associated fittings; replacement of the diagonal brace assembly on certain airplanes; and applicable related investigative and corrective actions. We are proposing [[Page 26384]] this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by July 23, 2018. 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 http://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, Transport Standards 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 on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0504. Examining the AD Docket You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018- 0504; 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, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (phone: 800-647- 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Jeffrey Chang, Aerospace Engineer, Propulsion Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5263; fax: 562-627- 5210; email: [email protected] or George Garrido, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5232; fax: 562-627- 5210; email [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2018-0504; Product Identifier 2018-NM-046-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this NPRM. Discussion We have received reports of cracking of the midspar fittings and of the engine and nacelle strut separating from the airplane. We issued AD 2012-16-12, Amendment 39-16159 (77 FR 49708, August 17, 2012) to require inspection of the inboard and outboard strut midspar fittings and AD 2015-11-04, Amendment 39-18167 (80 FR 30605, May 29, 2015) to require replacement of all engine strut midspar fittings and to initiate a life limit program. Since that time, we have determined that inspections of other strut fittings are needed for timely detection of cracking. Cracks have been reported in the diagonal brace end fittings, forward mating fittings, aft mating fittings, overwing support fittings, and the upper surface and the aft lug(s) of the front spar fittings on the nacelle struts, numbers 1, 2, 3 and 4. This cracking is attributed to fatigue in the end fittings and stress corrosion or fatigue in the mating fittings. This condition, if not addressed, could result in cracks that grow beyond a critical length, allowing strut fittings to fail and reducing the structural integrity of the nacelle. This, in combination with damage to adjacent attachment structure, could result in the loss of an engine from the airplane. Related Service Information Under 1 CFR Part 51 We reviewed the following service information. Boeing 707 Alert Service Bulletin A3364, Revision 4, dated February 21, 2017. The service information describes procedures for repetitive detailed inspections of the diagonal brace tube for any crack; repetitive detailed inspections and high frequency eddy current (HFEC) inspections of the nacelle strut diagonal brace end fittings, forward mating fitting, and aft mating fitting for any crack; an alternative dye penetrant inspection of vertical webs on aft mating fitting for any crack; an HFEC inspection of the diagonal brace tube for any crack; and corrective actions. Boeing 707 Alert Service Bulletin A3365, Revision 3, dated March 9, 2017. The service information describes procedures for repetitive detailed, HFEC, and ultrasonic inspections of the overwing support fittings for any crack at the bolt hole forward of the wing front spar and at the holes for the four fasteners attaching the fitting to the spar, and related investigative and corrective actions. Boeing 707 Alert Service Bulletin A3514, Revision 1, dated November 9, 2016. The service information describes procedures for repetitive detailed and surface HFEC inspections of the front spar fittings at nacelle struts numbers 1, 2, 3, and 4 for cracks, and replacement of cracked front spar fittings. 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. FAA's Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of these same type designs. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ``Differences Between this Proposed AD and the Service Information.'' For information on the procedures and compliance times, see this service information at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0504. The phrase ``related investigative actions'' is used in this proposed AD. Related investigative actions are follow-on actions that (1) are related to the primary action, and (2) further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. The phrase ``corrective actions'' is used in this proposed AD. Corrective actions correct or address any condition found. Corrective actions in an AD could include, for example, repairs. [[Page 26385]] Differences Between This Proposed AD and the Service Information Boeing 707 Alert Service Bulletin A3364, Revision 4, dated February 21, 2017; Boeing 707 Alert Service Bulletin A3365, Revision 3, dated March 9, 2017; and Boeing 707 Alert Service Bulletin A3514, Revision 1, dated November 9, 2016; specify to contact the manufacturer for certain instructions, but this proposed AD would require using repair methods, modification deviations, replacement deviations, and alteration deviations in one of the following ways: In accordance with a method that we approve; or Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Costs of Compliance We estimate that this proposed AD affects 65 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Detailed inspections per Service 36 work-hours x $85 $0 $3,060 per $198,900 per Bulletin A3364, Revision 4. per hour = $3,060 inspection cycle. inspection cycle. per inspection cycle. HFEC inspections per Service 128 work-hours x 0 $10,880 per $707,200 per Bulletin A3364, Revision 4. $85 per hour = inspection cycle. inspection cycle. $10,880 per inspection cycle. Inspections per Service Bulletin 20 work-hours x $85 0 $1,700 per $110,500 per A3365, Revision 3. per hour = $1,700 inspection cycle. inspection cycle. per inspection cycle. Detailed inspections per Service 12 work-hours x $85 0 $1,020 per $66,300 per Bulletin A3514, Revision 1. per hour = $1,020 inspection cycle. inspection cycle. per inspection cycle. HFEC inspections per Service 32 work-hours x $85 0 $2,720 per $176,800 per Bulletin A3514, Revision 1. per hour = $2,720 inspection cycle. inspection cycle. per inspection cycle. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. We estimate that any necessary proposed replacement of affected fittings would take about 96 work-hours for a cost of $8,160 per fitting. We have received no definitive data on the parts costs of the affected fittings. We have no way of determining the number of aircraft that might need this replacement. 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. We are 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. This proposed AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes and associated appliances to the Director of the System Oversight Division. Regulatory Findings We 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 this proposed regulation: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The 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 adding the following new airworthiness directive (AD): The Boeing Company: Docket No. FAA-2018-0504; Product Identifier 2018-NM-046-AD. (a) Comments Due Date We must receive comments by July 23, 2018. (b) Affected ADs This AD affects AD 82-24-03, Amendment 39-4496 (47 FR 51099, November 12, 1982) (``AD 82-24-03'') and AD 2005-08-15, Amendment 39-14067 (70 FR 21136, April 25, 2005) (``AD 2005-08-15''). (c) Applicability This AD applies to all The Boeing Company Model 707-100 Long Body, -200, -100B Long Body, and -100B Short Body series airplanes; Model 707-300, -300B, -300C, and -400 series airplanes; and Model 720 and 720B series airplanes; certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 54, Nacelles/ pylons. [[Page 26386]] (e) Unsafe Condition This AD was prompted by a report indicating that a fracture of the midspar fitting resulted in the separation of the inboard strut and engine from the airplane, and a determination that existing inspections for other nacelle strut fittings are not sufficient for timely detection of cracking. We are issuing this AD to address cracks, which if not detected and corrected, could grow beyond a critical length, allowing the strut fitting to fail and reducing the structural integrity of the nacelle. This, in combination with damage to adjacent attachment structure, could result in the loss of an engine from the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Detailed Inspections of the Front Spar Fittings at Nacelle Struts Numbers 1, 2, 3, and 4 Prior to the accumulation of 3,500 total flight hours; within 700 flight hours after the most recent inspection specified in Boeing 707 Alert Service Bulletin A3514, dated July 29, 2004, was done; or within three months after the effective date of this AD; whichever occurs later: Do a detailed inspection for cracking of the front spar fittings at nacelle struts numbers 1, 2, 3, and 4, in accordance with the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3514, Revision 1, dated November 9, 2016. If any cracking is found, before further flight, replace the affected fitting, in accordance with the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3514, Revision 1, dated November 9, 2016. Repeat the inspections thereafter at intervals not to exceed 700 flight hours. (h) Repetitive Surface High Frequency Eddy Current (HFEC) Inspections of the Aft Lugs on the Front Spar Fittings at Nacelle Struts Numbers 1, 2, 3, and 4 Within 1,500 flight cycles or 48 months after the most recent detailed inspection required by paragraph (g) of this AD was done, whichever occurs first, do a surface HFEC inspection for cracking of the aft lugs on the front spar fittings at nacelle struts numbers 1, 2, 3, and 4, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3514, Revision 1, dated November 9, 2016, except as required by paragraph (l)(4) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection thereafter at intervals not to exceed 1,500 flight cycles or 48 months, whichever occurs first. (i) Repetitive Inspections of the Overwing Support Fitting at Nacelle Struts Numbers 1, 2, 3, and 4 At the times specified in paragraph 1.E., ``Compliance,'' of Boeing 707 Alert Service Bulletin A3365, Revision 3, dated March 9, 2017, except as required by paragraph (l)(1) of this AD: Do the inspections specified in paragraphs (i)(1) through (i)(3) of this AD and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3365, Revision 3, dated March 9, 2017, except as required by paragraph (l)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections thereafter at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing 707 Alert Service Bulletin A3365, Revision 3, dated March 9, 2017. (1) Do a detailed inspection for any crack at all five holes in the overwing support fitting, and at the flange radii. (2) Do the inspection specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD. (i) Do a surface HFEC inspection for any crack in the overwing support fitting around the hole immediately forward of the spar chord, with the bolt in place, and at the flange radii. (ii) Do an open hole HFEC inspection for any crack in the overwing support fitting at the hole immediately forward of the spar chord. (3) Do the inspection specified in paragraph (i)(3)(i) or (i)(3)(ii) of this AD. (i) Do an ultrasonic inspection for any crack in the overwing support fitting around the four holes common to the fitting and the spar chord, with the bolts in place. (ii) Do a surface HFEC inspection for any crack in the overwing support fitting around the four holes common to the fitting and the spar chord, with the bolts in place. (j) Inspections of the Nacelle Strut Diagonal Braces and Associated Fittings For airplanes with nacelle strut diagonal braces and associated fittings which have accumulated 7,500 flight cycles or more: At the applicable times specified in paragraph 1.E., ``Compliance'' of Boeing 707 Alert Service Bulletin A3364, Revision 4, dated February 21, 2017, except as required by paragraph (l)(2) of this AD, do the inspections specified in paragraphs (j)(1) through (j)(3) of this AD. Repeat the inspections thereafter at the applicable intervals specified in tables 1, 2, 3, and 4 of paragraph 1.E., ``Compliance,'' of Boeing 707 Alert Service Bulletin A3364, Revision 4, dated February 21, 2017. If any crack is found during any inspection required by this paragraph, before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3364, Revision 4, dated February 21, 2017, except as required by paragraph (l)(3) of this AD. (1) Do a detailed inspection of the nacelle strut diagonal brace end fittings, diagonal brace tube, forward mating fitting, and aft mating fitting for any crack. (2) Do HFEC inspections of the nacelle strut diagonal brace end fittings, forward mating fitting, and aft mating fitting for any crack. As an alternative for the aft mating fitting, do a dye penetrant inspection of vertical webs on aft mating fitting for any crack. (3) Do an HFEC inspection of the diagonal brace tube for any crack. (k) Replacement For Group 3, 4, and 6 airplanes as identified in Boeing 707 Alert Service Bulletin A3364, Revision 4, dated February 21, 2017, on which the outboard diagonal brace end fitting (forward or aft) attach holes have been oversized as specified in Boeing 707 Alert Service Bulletin A3364, Revision 4, dated February 21, 2017: Within 1,000 flight cycles after the effective date of this AD, replace the diagonal brace assembly, in accordance with Figure 3 of Boeing 707 Alert Service Bulletin A3364, Revision 4, dated February 21, 2017. (l) Exceptions to Service Information Specifications (1) For purposes of determining compliance with the requirements of this AD: Where Boeing 707 Alert Service Bulletin A3365, Revision 3, dated March 9, 2017, uses the phrase ``the Revision 3 date of this service bulletin,'' this AD requires using ``the effective date of this AD.'' (2) For purposes of determining compliance with the requirements of this AD: Where Boeing 707 Alert Service Bulletin A3364, Revision 4, dated February 21, 2017, uses the phrase ``the Revision 4 date of this service bulletin,'' this AD requires using ``the effective date of this AD.'' (3) Where Boeing 707 Alert Service Bulletin A3364, Revision 4, dated February 21, 2017; and Boeing 707 Alert Service Bulletin A3365, Revision 3, dated March 9, 2017; specify contacting Boeing: This AD requires repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. (4) Where Boeing 707 Alert Service Bulletin A3514, Revision 1, dated November 9, 2016, specifies contacting Boeing: This AD requires replacement using a method approved in accordance with the procedures specified in paragraph (o) of this AD. (m) Terminating Action for Other ADs (1) Accomplishing the initial inspections required by paragraph (j) of this AD terminates all requirements of AD 82-24-03. (2) Accomplishing the initial inspections required by paragraph (g) of this AD, terminates all requirements of AD 2005-08-15. (n) Parts Installation Prohibition As of the effective date of this AD, no person may install, on any airplane, a front spar fitting having a part number other than the part numbers specified in paragraph 2.C.2. of Boeing 707 Alert Service Bulletin A3514, Revision 1, dated November 9, 2016. (o) 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(s) identified in paragraph (p)(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 [[Page 26387]] of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, replacement, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO Branch, to make those findings. To be approved, the repair method, modification deviation, replacement deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (p) Related Information (1) For more information about this AD, contact Jeffrey Chang, Aerospace Engineer, Propulsion Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627- 5263; fax: 562-627-5210; email: [email protected] or George Garrido, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5232; fax: 562-627-5210; 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 service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. Issued in Des Moines, Washington, on May 24, 2018. James Cashdollar, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-12128 Filed 6-6-18; 8:45 am] BILLING CODE 4910-13-P
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(c) Applicability (j) Optional Terminating Action for Inserting (ii) Steps not labeled as RC may be
This AD applies to Honda Aircraft the AFM Temporary Revision/Pilot Checks deviated from using accepted methods in
Company LLC Model HA–420 airplanes, all (1) Instead of inserting the temporary accordance with the operator’s maintenance
serial numbers, that: revision or at any time after inserting the or inspection program without obtaining
(1) Have power brake valve, part number temporary revision required by paragraph (g) approval of an AMOC, provided the RC steps,
of this AD and before the mandatory including substeps and identified figures, can
(P/N) HJ1–13243–101–005 or HJ1–13243–
replacement required in paragraph (j) of this still be done as specified, and the airplane
101–007, installed; and
AD, you may replace the installed PBV, P/N can be put back in an airworthy condition.
(2) are certificated in any category.
HJ1–13243–101–005 or P/N HJ1–13243–101– (n) Related Information
(d) Subject 007, with the improved design PBV, P/N
HJ1–13243–101–009. The replacement must (1) For more information about this AD,
Joint Aircraft System Component (JASC)/ contact Samuel Kovitch, Aerospace Engineer,
Air Transport Association (ATA) of America be done using the Accomplishment
Instructions in either Honda Service Bulletin Atlanta ACO Branch, FAA, 1701 Columbia
Code 32, Landing Gear. Avenue, College Park, Georgia 30337; phone:
SB–420–32–001, dated January 8, 2018, or
(e) Unsafe Condition Revision B, dated April 16, 2018. Before (404) 474–5570; fax: (404) 474–5605; email:
further flight after installing P/N HJ1–13243– samuel.kovitch@faa.gov.
This AD was prompted by reports of
101–009, remove the temporary revision from (2) For service information identified in
unannunciated asymmetric braking during
the Honda HA–420 AFM. this AD, contact Honda Aircraft Company
ground operations and landing deceleration.
(2) The on-condition replacement required LLC, 6430 Ballinger Road, Greensboro, North
We are issuing this AD to detect failure of the
by paragraph (h) of this AD is still required Carolina 27410; telephone (336) 662–0246;
power brake valve (PBV). The unsafe
before further flight. internet: http://www.hondajet.com. FAA,
condition, if not addressed, could result in
Policy and Innovation Division, 901 Locust,
degraded braking performance and reduced (k) Mandatory Replacement Kansas City, Missouri 64106. For information
directional control during ground operations
Within the next 12 months after the on the availability of this material at the
and landing deceleration.
effective date of this AD, replace the installed FAA, call (816) 329–4148.
(f) Compliance PBV, P/N HJ1–13243–101–005 or P/N HJ1–
Issued in Kansas City, Missouri, on May
Comply with this AD within the 13243–101–007, with the improved design
29, 2018.
compliance times specified, unless already PBV, P/N HJ1–13243–101–009. The
replacement must be done using the Melvin J. Johnson,
done.
Accomplishment Instructions in either Aircraft Certification Service, Deputy
(g) Insert Temporary Revision Into the Honda Service Bulletin SB–420–32–001, Director, Policy and Innovation Division,
Airplane Flight Manual (AFM) dated January 8, 2018, or Revision B, dated AIR–601.
Before further flight after May 29, 2018 (the April 16, 2018. Before further flight after [FR Doc. 2018–12127 Filed 6–6–18; 8:45 am]
installing P/N HJ1–13243–101–009, remove
effective date retained from AD 2018–11–05) BILLING CODE 4910–13–P
the temporary revision from the Honda HA–
insert Honda Aircraft Company Temporary
420 AFM.
Revision TR 01.1, dated February 16, 2018,
into the Honda Aircraft Company (Honda) (l) Special Flight Permit DEPARTMENT OF TRANSPORTATION
HA–420 Airplane Flight Manual (AFM) (‘‘the Special flight permits for the AFM
temporary revision’’). The procedures listed Limitations portion of this AD are prohibited. Federal Aviation Administration
in the temporary revision are required while Special flight permits for the PBV
operating with PBV P/N HJ1–13243–101–005 replacement required in this AD are 14 CFR Part 39
or P/N HJ1–13243–101–007 installed. This permitted with the following limitations: One
insertion and the steps therein may be ferry flight, including fuel stops, to service [Docket No. FAA–2018–0504; Product
performed by the owner/operator (pilot) center with Honda Aircraft Company Identifier 2018–NM–046–AD]
holding at least a private pilot certificate and Temporary Revision TR 01.1, dated February
must be entered into the airplane records RIN 2120–AA64
16, 2018, incorporated into the Honda HA–
showing compliance with this AD in 420 AFM.
accordance with 14 CFR 43.9(a)(1)–(4) and 14 Airworthiness Directives; The Boeing
CFR 91.417(a)(2)(v). The record must be (m) Alternative Methods of Compliance Company Airplanes
maintained as required by 14 CFR 91.417, (AMOCs)
AGENCY: Federal Aviation
121.380, or 135.439. (1) The Manager, Atlanta ACO Branch,
FAA, has the authority to approve AMOCs
Administration (FAA), DOT.
(h) No Reporting Requirement ACTION: Notice of proposed rulemaking
for this AD, if requested using the procedures
Although Honda Service Bulletin SB–420– found in 14 CFR 39.19. In accordance with (NPRM).
32–001, dated January 8, 2018, and Revision 14 CFR 39.19, send your request to your
B, dated April 16, 2018, specify submitting principal inspector or local Flight Standards SUMMARY: We propose to adopt a new
certain information to the manufacturer, this District Office, as appropriate. If sending airworthiness directive (AD) for all The
AD does not require that action. information directly to the manager of the Boeing Company Model 707 series
certification office, send it to the attention of airplanes and Model 720 and 720B
(i) Replace the Power Brake Valve
the person identified in paragraph (n) of this series airplanes. This proposed AD was
As of and at any time after May 29, 2018 AD.
(the effective date retained from AD 2018– prompted by a report indicating that a
(2) Before using any approved AMOC,
11–05), if any of the procedures listed in the notify your appropriate principal inspector,
fracture of the midspar fitting resulted
temporary revision referenced in paragraph or lacking a principal inspector, the manager in the separation of the inboard strut
(g) of this AD reveal a leaking PBV, before of the local flight standards district office/ and engine from the airplane, and a
further flight, replace the installed PBV, P/N certificate holding district office. determination that existing inspections
HJ1–13243–101–005 or P/N HJ1–13243–101– (3) For service information that contains are not sufficient for timely detection of
sradovich on DSK3GMQ082PROD with PROPOSALS
007, with the improved design PBV, P/N steps that are labeled as Required for cracking. This proposed AD would
HJ1–13243–101–009. The replacement must Compliance (RC), the provisions of require repetitive inspections of certain
be done using the Accomplishment paragraphs (h) through (j) of this AD apply. nacelle strut spar and overwing fittings,
Instructions in either Honda Service Bulletin (i) The steps labeled as RC, including
SB–420–32–001, dated January 8, 2018, or substeps under an RC step and any figures
and diagonal braces and associated
Revision B, dated April 16, 2018. Before identified in an RC step, must be done to fittings; replacement of the diagonal
further flight after installing P/N HJ1–13243– comply with the AD. An AMOC is required brace assembly on certain airplanes; and
101–009, remove the temporary revision from for any deviations to RC steps, including applicable related investigative and
the Honda HA–420 AFM. substeps and identified figures. corrective actions. We are proposing
VerDate Sep<11>2014 15:57 Jun 06, 2018 Jkt 244001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 E:\FR\FM\07JNP1.SGM 07JNP1](https://thefederalregister.org/doc/83_FR_26493/page/1.svg)
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Differences Between This Proposed AD but this proposed AD would require Commercial Airplanes Organization
and the Service Information using repair methods, modification Designation Authorization (ODA) whom
Boeing 707 Alert Service Bulletin deviations, replacement deviations, and we have authorized to make those
A3364, Revision 4, dated February 21, alteration deviations in one of the findings.
2017; Boeing 707 Alert Service Bulletin following ways:
Costs of Compliance
A3365, Revision 3, dated March 9, 2017; • In accordance with a method that
and Boeing 707 Alert Service Bulletin we approve; or We estimate that this proposed AD
A3514, Revision 1, dated November 9, • Using data that meet the affects 65 airplanes of U.S. registry. We
2016; specify to contact the certification basis of the airplane, and estimate the following costs to comply
manufacturer for certain instructions, that have been approved by the Boeing with this proposed AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Detailed inspections per Service Bulletin 36 work-hours × $85 per hour = $3,060 $0 $3,060 per inspec- $198,900 per in-
A3364, Revision 4. per inspection cycle. tion cycle. spection cycle.
HFEC inspections per Service Bulletin 128 work-hours × $85 per hour = 0 $10,880 per inspec- $707,200 per in-
A3364, Revision 4. $10,880 per inspection cycle. tion cycle. spection cycle.
Inspections per Service Bulletin A3365, 20 work-hours × $85 per hour = $1,700 0 $1,700 per inspec- $110,500 per in-
Revision 3. per inspection cycle. tion cycle. spection cycle.
Detailed inspections per Service Bulletin 12 work-hours × $85 per hour = $1,020 0 $1,020 per inspec- $66,300 per inspec-
A3514, Revision 1. per inspection cycle. tion cycle. tion cycle.
HFEC inspections per Service Bulletin 32 work-hours × $85 per hour = $2,720 0 $2,720 per inspec- $176,800 per in-
A3514, Revision 1. per inspection cycle. tion cycle. spection cycle.
We have received no definitive data FAA Order 8000.51C. In accordance The Proposed Amendment
that would enable us to provide cost with that order, issuance of ADs is Accordingly, under the authority
estimates for the on-condition actions normally a function of the Compliance delegated to me by the Administrator,
specified in this proposed AD. and Airworthiness Division, but during the FAA proposes to amend 14 CFR part
We estimate that any necessary this transition period, the Executive 39 as follows:
proposed replacement of affected Director has delegated the authority to
fittings would take about 96 work-hours issue ADs applicable to transport PART 39—AIRWORTHINESS
for a cost of $8,160 per fitting. We have category airplanes and associated DIRECTIVES
received no definitive data on the parts appliances to the Director of the System
costs of the affected fittings. We have no Oversight Division. ■ 1. The authority citation for part 39
way of determining the number of continues to read as follows:
aircraft that might need this Regulatory Findings
Authority: 49 U.S.C. 106(g), 40113, 44701.
replacement. We determined that this proposed AD
would not have federalism implications § 39.13 [Amended]
Authority for This Rulemaking
under Executive Order 13132. This ■ 2. The FAA amends § 39.13 by adding
Title 49 of the United States Code proposed AD would not have a the following new airworthiness
specifies the FAA’s authority to issue substantial direct effect on the States, on directive (AD):
rules on aviation safety. Subtitle I, the relationship between the national
section 106, describes the authority of The Boeing Company: Docket No. FAA–
Government and the States, or on the 2018–0504; Product Identifier 2018–
the FAA Administrator. Subtitle VII: distribution of power and NM–046–AD.
Aviation Programs, describes in more responsibilities among the various
detail the scope of the Agency’s levels of government. (a) Comments Due Date
authority. For the reasons discussed above, I We must receive comments by July 23,
We are issuing this rulemaking under certify this proposed regulation: 2018.
the authority described in Subtitle VII, (1) Is not a ‘‘significant regulatory (b) Affected ADs
Part A, Subpart III, Section 44701: action’’ under Executive Order 12866,
‘‘General requirements.’’ Under that (2) Is not a ‘‘significant rule’’ under This AD affects AD 82–24–03, Amendment
section, Congress charges the FAA with 39–4496 (47 FR 51099, November 12, 1982)
the DOT Regulatory Policies and (‘‘AD 82–24–03’’) and AD 2005–08–15,
promoting safe flight of civil aircraft in Procedures (44 FR 11034, February 26, Amendment 39–14067 (70 FR 21136, April
air commerce by prescribing regulations 1979), 25, 2005) (‘‘AD 2005–08–15’’).
for practices, methods, and procedures (3) Will not affect intrastate aviation
the Administrator finds necessary for in Alaska, and (c) Applicability
safety in air commerce. This regulation (4) Will not have a significant This AD applies to all The Boeing
is within the scope of that authority economic impact, positive or negative, Company Model 707–100 Long Body, –200,
sradovich on DSK3GMQ082PROD with PROPOSALS
because it addresses an unsafe condition on a substantial number of small entities –100B Long Body, and –100B Short Body
that is likely to exist or develop on under the criteria of the Regulatory series airplanes; Model 707–300, –300B,
products identified in this rulemaking –300C, and –400 series airplanes; and Model
Flexibility Act. 720 and 720B series airplanes; certificated in
action. any category.
This proposed AD is issued in List of Subjects in 14 CFR Part 39
accordance with authority delegated by Air transportation, Aircraft, Aviation (d) Subject
the Executive Director, Aircraft safety, Incorporation by reference, Air Transport Association (ATA) of
Certification Service, as authorized by Safety. America Code 54, Nacelles/pylons.
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![Federal Register / Vol. 83, No. 110 / Thursday, June 7, 2018 / Proposed Rules 26387
of the local flight standards district office/
and MBB–BK 117 D–2 helicopters. This Comments Invited
certificate holding district office. proposed AD would require altering and
(3) An AMOC that provides an acceptable re-identifying the overhead panel shock We invite you to participate in this
level of safety may be used for any repair, mount assembly (shock mount). This rulemaking by submitting written
modification, replacement, or alteration comments, data, or views. We also
required by this AD if it is approved by the
proposed AD is prompted by the
manufacturer’s stress recalculations. invite comments relating to the
Boeing Commercial Airplanes Organization economic, environmental, energy, or
Designation Authorization (ODA) that has The actions of this proposed AD are
intended to correct an unsafe condition federalism impacts that might result
been authorized by the Manager, Los Angeles
ACO Branch, to make those findings. To be on these products. from adopting the proposals in this
approved, the repair method, modification document. The most helpful comments
DATES: We must receive comments on
deviation, replacement deviation, or reference a specific portion of the
this proposed AD by August 6, 2018. proposal, explain the reason for any
alteration deviation must meet the
certification basis of the airplane, and the ADDRESSES: You may send comments by recommended change, and include
approval must specifically refer to this AD. any of the following methods: supporting data. To ensure the docket
(p) Related Information • Federal eRulemaking Docket: Go to does not contain duplicate comments,
http://www.regulations.gov. Follow the commenters should send only one copy
(1) For more information about this AD,
online instructions for sending your of written comments, or if comments are
contact Jeffrey Chang, Aerospace Engineer,
Propulsion Section, FAA, Los Angeles ACO comments electronically. filed electronically, commenters should
Branch, 3960 Paramount Boulevard, • Fax: 202–493–2251. submit only one time.
Lakewood, CA 90712–4137; phone: 562–627– • Mail: Send comments to the U.S. We will file in the docket all
5263; fax: 562–627–5210; email: Department of Transportation, Docket comments that we receive, as well as a
jeffrey.chang@faa.gov or George Garrido, Operations, M–30, West Building report summarizing each substantive
Aerospace Engineer, Airframe Section, FAA, Ground Floor, Room W12–140, 1200
Los Angeles ACO Branch, 3960 Paramount
public contact with FAA personnel
New Jersey Avenue SE, Washington, DC concerning this proposed rulemaking.
Boulevard, Lakewood, CA 90712–4137;
20590–0001. Before acting on this proposal, we will
phone: 562–627–5232; fax: 562–627–5210;
email george.garrido@faa.gov. • Hand Delivery: Deliver to the consider all comments we receive on or
(2) For service information identified in ‘‘Mail’’ address between 9 a.m. and 5 before the closing date for comments.
this AD, contact Boeing Commercial p.m., Monday through Friday, except We will consider comments filed after
Airplanes, Attention: Contractual & Data Federal holidays. the comment period has closed if it is
Services (C&DS), 2600 Westminster Blvd., possible to do so without incurring
MC 110–SK57, Seal Beach, CA 90740–5600; Examining the AD Docket
expense or delay. We may change this
telephone 562–797–1717; internet https:// You may examine the AD docket on
www.myboeingfleet.com. You may view this
proposal in light of the comments we
the internet at http:// receive.
service information at the FAA, Transport
www.regulations.gov by searching for
Standards Branch, 2200 South 216th St., Des Discussion
Moines, WA. For information on the and locating Docket No. FAA–2018–
availability of this material at the FAA, call 0517; or in person at Docket Operations EASA, which is the Technical Agent
206–231–3195. between 9 a.m. and 5 p.m., Monday for the Member States of the European
through Friday, except Federal holidays. Union, has issued EASA AD No. 2017–
Issued in Des Moines, Washington, on May
24, 2018. The AD docket contains this proposed 0026, dated February 14, 2017, to
AD, the European Aviation Safety correct an unsafe condition for Airbus
James Cashdollar,
Agency (EASA) AD, the economic Helicopters Model MBB–BK 117 C–2,
Acting Director, System Oversight Division,
evaluation, any comments received, and MBB–BK117 C–2e, MBB–BK 117 D–2,
Aircraft Certification Service.
other information. The street address for and MBB–BK117 D–2m helicopters.
[FR Doc. 2018–12128 Filed 6–6–18; 8:45 am]
Docket Operations (telephone 800–647– EASA advises that a recent stress
BILLING CODE 4910–13–P
5527) is in the ADDRESSES section. calculation identified that the shock
Comments will be available in the AD mount may not withstand certification
docket shortly after receipt. crash loads. EASA states that this
DEPARTMENT OF TRANSPORTATION
For service information identified in condition, if not corrected, could lead to
Federal Aviation Administration this proposed rule, contact Airbus the overhead panel disconnecting
Helicopters, 2701 N. Forum Drive, during an emergency landing and
14 CFR Part 39 Grand Prairie, TX 75052; telephone injuring occupants. Accordingly, the
(972) 641–0000 or (800) 232–0323; fax EASA AD requires modifying and re-
[Docket No. FAA–2018–0517; Product (972) 641–3775; or at http://
Identifier 2017–SW–098–AD] identifying the shock mounts.
www.helicopters.airbus.com/website/
RIN 2120–AA64 en/ref/Technical-Support_73.html. You FAA’s Determination
may review the referenced service
These helicopters have been approved
Airworthiness Directives; Airbus information at the FAA, Office of the
by the aviation authority of Germany
Helicopters Deutschland GmbH Regional Counsel, Southwest Region,
and are approved for operation in the
Helicopters 10101 Hillwood Pkwy, Room 6N–321,
United States. Pursuant to our bilateral
Fort Worth, TX 76177.
AGENCY: Federal Aviation agreement with Germany, EASA, its
sradovich on DSK3GMQ082PROD with PROPOSALS
Administration (FAA), DOT. FOR FURTHER INFORMATION CONTACT: Matt technical representative, has notified us
Fuller, Senior Aviation Safety Engineer, of the unsafe condition described in its
ACTION: Notice of proposed rulemaking
Safety Management Section, Rotorcraft AD. We are proposing this AD because
(NPRM).
Standards Branch, FAA, 10101 we evaluated all known relevant
SUMMARY: We propose to adopt a new Hillwood Pkwy., Fort Worth, TX 76177; information and determined that an
airworthiness directive (AD) for Airbus telephone (817) 222–5110; email unsafe condition is likely to exist or
Helicopters Deutschland GmbH (Airbus matthew.fuller@faa.gov. develop on other products of the same
Helicopters) Model MBB–BK 117 C–2 SUPPLEMENTARY INFORMATION: type design.
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Document Created: 2018-06-07 00:50:19
Document Modified: 2018-06-07 00:50:19
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by July 23, 2018. | |
| Contact | Jeffrey Chang, Aerospace Engineer, Propulsion Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5263; fax: 562-627- 5210; email: [email protected] or George Garrido, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5232; fax: 562-627- 5210; email [email protected] | |
| FR Citation | 83 FR 26383 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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