83 FR 46902 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 180 (September 17, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 180 (September 17, 2018)
| Page Range | 46902-46905 | |
| FR Document | 2018-19840 |
[Federal Register Volume 83, Number 180 (Monday, September 17, 2018)] [Proposed Rules] [Pages 46902-46905] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-19840] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0793; Product Identifier 2018-NM-057-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- [[Page 46903]] SUMMARY: We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This proposed AD was prompted by a report of cracks in the body station (STA) 303.9 frame web and doubler at fastener holes common to the stop fitting at stringer 16 left (S-16L). This proposed AD would require repetitive surface high frequency eddy current (HFEC) inspections for cracking of the STA 303.9 frame web and doubler at the stop fitting at S-16L, and applicable on-condition actions. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by November 1, 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; phone: 562-797-1717; internet: https://www.myboeingfleet.com. You may view this referenced 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-2018-0793. 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- 0793; 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: Galib Abumeri, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; 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-2018-0793; Product Identifier 2018-NM-057-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 proposed AD. Discussion We have received a report indicating cracks in the STA 303.9 frame web and doubler at fastener holes common to the stop fitting at S-16L. The cracks were found during accomplishment of Boeing Service Bulletin 737-53A1188. We have determined that the existing inspection programs are not sufficient to find any crack in the STA 303.9 frame web and doubler at the stop fitting at S-16L. This condition, if not addressed, could result in the inability of a principal structural element to sustain limit loads and possible rapid decompression of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Requirements Bulletin 737-53A1375 RB, dated March 12, 2018. The service information describes procedures for repetitive surface HFEC inspections for cracking of the STA 303.9 frame web and doubler at the stop fitting at S-16L, and applicable on- condition actions. 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 the same type design. Proposed AD Requirements This proposed AD would require accomplishment of the actions identified in Boeing Requirements Bulletin 737-53A1375 RB, dated March 12, 2018, described previously, except for any differences identified as exceptions in the regulatory text of this proposed AD. 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-2018-0793. Explanation of Applicability Model 737 airplanes having line numbers 1 through 291 have a limit of validity (LOV) of 34,000 total flight cycles, and the actions proposed in this NPRM, as specified in Boeing Requirements Bulletin 737-53A1375 RB, dated March 12, 2018, would be required at a compliance time occurring after that LOV. Although operation of an airplane beyond its LOV is prohibited by 14 CFR 121.1115 and 129.115, this NPRM would include those airplanes in the applicability so that these airplanes are tracked in the event the LOV is extended in the future. Explanation of Requirements Bulletin The FAA worked in conjunction with industry, under the Airworthiness Directives Implementation Aviation Rulemaking Committee (AD ARC), to enhance the AD system. One enhancement is a process for annotating which steps in the service information are ``required for compliance'' (RC) with an AD. Boeing has implemented this RC concept into Boeing service bulletins. In an effort to further improve the quality of ADs and AD-related Boeing service information, a joint process improvement initiative was worked between the FAA and Boeing. The initiative resulted in the development of a new process in which the service information more clearly identifies the actions needed to address the unsafe condition in the ``Accomplishment Instructions.'' The new process results in a Boeing Requirements Bulletin, which contains only the actions needed to address the unsafe condition (i.e., only the RC actions). [[Page 46904]] Costs of Compliance We estimate that this proposed AD affects 67 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs for Required Actions ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- HFEC Inspections................. 13 work-hours x $85 $0 $1,105 per $74,035 per per hour = $1,105 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. 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-2018-0793; Product Identifier 2018-NM-057-AD. (a) Comments Due Date We must receive comments by November 1, 2018. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 737-100, -200, - 200C, -300, -400, and -500 series airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by a report of cracks in the body station (STA) 303.9 frame web and doubler at fastener holes common to the stop fitting at stringer 16 left (S-16L). We are issuing this AD to address cracks in the STA 303.9 frame web and doubler at the stop fitting at S-16L, which, if not addressed, could result in the inability of a principal structural element to sustain limit loads and possible rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions for Group 1 For airplanes identified as Group 1 in Boeing Requirements Bulletin 737-53A1375 RB, dated March 12, 2018: Within 120 days after the effective date of this AD, inspect the airplane and do all applicable on-condition actions using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (h) Required Actions for Groups 2 Through 5 Except as specified in paragraph (i) of this AD: For airplanes identified as Groups 2 through 5 in Boeing Requirements Bulletin 737-53A1375 RB, dated March 12, 2018, at the applicable times specified in the ``Compliance'' paragraph of Boeing Requirements Bulletin 737-53A1375 RB, dated March 12, 2018, do all applicable actions identified in, and in accordance with, the Accomplishment Instructions of Boeing Requirements Bulletin 737-53A1375 RB, dated March 12, 2018. Note 1 to paragraph (h) of this AD: Guidance for accomplishing the actions required by this AD can be found in Boeing Alert Service Bulletin 737-53A1375, dated March 12, 2018, which is referred to in Boeing Requirements Bulletin 737-53A1375 RB, dated March 12, 2018. (i) Exceptions to Service Information Specifications (1) For purposes of determining compliance with the requirements of this AD: Where Boeing Requirements Bulletin 737-53A1375 RB, dated March 12, 2018, uses the phrase ``the original issue date of Requirements Bulletin 737-53A1375 RB,'' this AD requires using ``the effective date of this AD.'' (2) Where Boeing Requirements Bulletin 737-53A1375 RB, dated March 12, 2018, specifies contacting Boeing for repair instructions, this AD requires repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD. [[Page 46905]] (j) 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 (k)(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 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, 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, 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. (k) Related Information (1) For more information about this AD, contact Galib Abumeri, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627- 5324; 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; phone: 562-797-1717; internet: https://www.myboeingfleet.com. You may view this referenced 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 August 30, 2018. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-19840 Filed 9-14-18; 8:45 am] BILLING CODE 4910-13-P
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(b) Affected ADs a crack, corrosion, or damage is found during (3) Reporting Requirements: A federal
None. any of the inspections, before further flight, agency may not conduct or sponsor, and a
do the applicable corrective actions (do person is not required to respond to, nor
(c) Applicability additional inspections, replace hardware, shall a person be subject to a penalty for
This AD applies to GA 8 Airvan (Pty) Ltd and replace any part with a crack, corrosion, failure to comply with a collection of
Models GA8 and GA8–TC320 airplanes, or damage). Follow the procedures in Parts information subject to the requirements of
certificated in any category, with a strut or C3 and D or E, as applicable, in the the Paperwork Reduction Act unless that
strut fitting installed that has a part number Accomplishment Instructions of GippsAero collection of information displays a currently
and serial number listed in table 1 of SB–GA8–2017–174, Issue 2. valid OMB Control Number. The OMB
GippsAero Service Bulletin SB–GA8–2017– (4) To use an eddy current or fluorescent Control Number for this information
174, Issue 2, dated May 23, 2018 (GippsAero liquid penetrant inspection method instead collection is 2120–0731. Public reporting for
SB–GA8–2017–174, Issue 2). of a visual inspection for the requirements in this collection of information is estimated to
paragraphs (f)(1) of this AD, the Manager, be approximately 1 hour per response,
(d) Subject Small Airplane Standards Branch, FAA must including the time for reviewing instructions,
Air Transport Association of America approve your inspection method, and the searching existing data sources, gathering
(ATA) Code 57: Wings. Manager’s approval letter must specifically and maintaining the data needed, completing
refer to this AD. Send your approval request and reviewing the collection of information.
(e) Reason to the contact information found in All responses to this collection of
This AD was prompted by mandatory paragraph (g)(1) of this AD. information are voluntary; the nature and
continuing airworthiness information (MCAI) (5) Remove from service each part listed in extent of confidentiality to be provided, if
issued by the aviation authority of another Parts D and E of table 3 on or before the part any. Send comments regarding this burden
country to identify and correct an unsafe exceeds its specified replacement time and estimate or any other aspect of this collection
condition on an aviation product. The MCAI replace with an airworthy part. On the of information, including suggestions for
describes the unsafe condition as certain effective date of this AD, any part listed in reducing this burden to: Information
wing strut fittings manufactured with table 3 of GippsAero SB–GA8–2017–174, Collection Clearance Officer, Federal
incorrect grain orientation, which has an Issue 2, that has exceeded its replacement Aviation Administration, 10101 Hillwood
unknown effect on fatigue-related concerns. time, within 100 hours TIS after the effective Parkway, Fort Worth, TX 76177–1524.
We are issuing this AD to detect and address date of this AD or within 12 months after the
fatigue-related damage to the wing strut effective date of this AD, whichever occurs (h) Related Information
fittings, which could lead to failure of the first, remove the part from service and Refer to MCAI issued by CASA, AD No.
wing with consequent loss of control of the replace with an airworthy part. Follow the AD/GA8/9, Amendment 1, dated May 29,
airplane. replacement procedures in Part D or Part E, 2018. You may examine the MCAI on the
as applicable, in the Accomplishment internet at http://www.regulations.gov by
(f) Actions and Compliance Instructions of GippsAero SB–GA8–2017– searching for and locating Docket No. FAA–
Unless already done, do the following 174, Issue 2. 2018–0771. For service information related to
actions in paragraphs (f)(1) through (6) of this (6) Within 24 hours after each inspection this AD, contact GA 8 Airvan (Pty) Ltd, c/o
AD: required in paragraphs (f)(1) and (2) of this GippsAero Pty Ltd, Attn: Technical Services,
(1) Within 3 months after the effective date AD, submit a report of the inspection results, P.O. Box 881, Morwell Victoria 3840,
of this AD or within 100 hours time-in- even if no damage is found, to the Civil Australia; telephone: +61 03 5172 1200; fax:
service (TIS) after the effective date of this Aviation Safety Authority (CASA) and GA 8 +61 03 5172 1201; email: aircraft.techpubs@
AD, whichever occurs first, with the wing Airvan (Pty) Ltd. Use the Document mahindraaerospace.com. You may review
struts removed, visually inspect each forward Compliance Notice of GippsAero SB–GA8– this referenced service information at the
and aft wing strut fitting and fuselage 2017–174, Issue 2, and include in the report FAA, Policy and Innovation Division, 901
attachment point for cracks, corrosion, and the total hours TIS on the airplane and the Locust, Kansas City, Missouri 64106. For
damage. If a crack, corrosion, or damage is type of operation. You may use the contact information on the availability of this
found during the inspection, before further information found in paragraph (h) of this material at the FAA, call (816) 329–4148.
flight, do the applicable corrective actions AD to contact GA 8 Airvan (Pty) Ltd. To
(check torque, restore surface protection, contact CASA, use the online CASA Defect Issued in Kansas City, Missouri, on August
rework areas with fouling, and replace any Reporting Service at the following internet 31, 2018.
part with a crack, corrosion, or damage). address: https://drs.casa.gov.au/. Melvin J. Johnson,
Follow the procedures in Parts C1, C2, and Deputy Director, Policy & Innovation Division,
D or E, as applicable, in the Accomplishment (g) Other FAA AD Provisions
Aircraft Certification Service.
Instructions in GippsAero SB–GA8–2017– The following provisions also apply to this
174, Issue 2. AD: [FR Doc. 2018–19889 Filed 9–14–18; 8:45 am]
(2) Within 3 months after the effective date (1) Alternative Methods of Compliance BILLING CODE 4910–13–P
of this AD or within 100 hours TIS after the (AMOCs): The Manager, Small Airplane
effective date of this AD, whichever occurs Standards Branch, FAA, has the authority to
first, and thereafter at intervals not to exceed approve AMOCs for this AD, if requested DEPARTMENT OF TRANSPORTATION
100 hours TIS, visually inspect each strut using the procedures found in 14 CFR 39.19.
and strut fitting for cracks, corrosion, and Send information to ATTN: Doug Rudolph, Federal Aviation Administration
damage. If a crack, corrosion, or damage is Aerospace Engineer, FAA, Small Airplane
found during any of the inspections, before Standards Branch, 901 Locust, Room 301, 14 CFR Part 39
further flight, do the applicable corrective Kansas City, Missouri 64106; telephone:
actions (check torque, restore surface (816) 329–4059; fax: (816) 329–4090; email: [Docket No. FAA–2018–0793; Product
protection, and replace any part with a crack, doug.rudolph@faa.gov. Before using any Identifier 2018–NM–057–AD]
corrosion, or damage). Follow the procedures approved AMOC on any airplane to which
in Parts B and D or E, as applicable, in the the AMOC applies, notify your appropriate RIN 2120–AA64
daltland on DSKBBV9HB2PROD with PROPOSALS
Accomplishment Instructions of GippsAero principal inspector (PI) in the FAA Flight
SB–GA8–2017–174, Issue 2. Standards District Office (FSDO), or lacking Airworthiness Directives; The Boeing
(3) Within 1,000 hours TIS after doing the a PI, your local FSDO. Company Airplanes
inspections required in paragraph (f)(1) of (2) Contacting the Manufacturer: For any
this AD and thereafter at intervals not to requirement in this AD to obtain corrective AGENCY: Federal Aviation
exceed 1,000 hours TIS, with the wing struts actions from a manufacturer, the action must Administration (FAA), DOT.
installed, visually inspect each forward and instead be accomplished using a method ACTION: Notice of proposed rulemaking
aft wing strut, strut fitting, and strut fitting approved by the Manager, Small Airplane (NPRM).
lug hole for cracks, corrosion, and damage. If Standards Branch, FAA; or CASA.
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Costs of Compliance estimate the following costs to comply
We estimate that this proposed AD with this proposed AD:
affects 67 airplanes of U.S. registry. We
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
HFEC Inspections ........ 13 work-hours × $85 per hour = $0 $1,105 per inspection cycle .... $74,035 per inspection cycle.
$1,105 per inspection cycle.
We have received no definitive data (1) Is not a ‘‘significant regulatory web and doubler at fastener holes common
that would enable us to provide cost action’’ under Executive Order 12866, to the stop fitting at stringer 16 left (S–16L).
estimates for the on-condition actions (2) Is not a ‘‘significant rule’’ under We are issuing this AD to address cracks in
the DOT Regulatory Policies and the STA 303.9 frame web and doubler at the
specified in this proposed AD.
stop fitting at S–16L, which, if not addressed,
Procedures (44 FR 11034, February 26, could result in the inability of a principal
Authority for This Rulemaking
1979), structural element to sustain limit loads and
Title 49 of the United States Code (3) Will not affect intrastate aviation possible rapid decompression of the airplane.
specifies the FAA’s authority to issue in Alaska, and
rules on aviation safety. Subtitle I, (4) Will not have a significant (f) Compliance
section 106, describes the authority of economic impact, positive or negative, Comply with this AD within the
the FAA Administrator. Subtitle VII: on a substantial number of small entities compliance times specified, unless already
Aviation Programs, describes in more under the criteria of the Regulatory done.
detail the scope of the Agency’s Flexibility Act. (g) Required Actions for Group 1
authority. For airplanes identified as Group 1 in
We are issuing this rulemaking under List of Subjects in 14 CFR Part 39
Boeing Requirements Bulletin 737–53A1375
the authority described in Subtitle VII, Air transportation, Aircraft, Aviation RB, dated March 12, 2018: Within 120 days
Part A, Subpart III, Section 44701: safety, Incorporation by reference, after the effective date of this AD, inspect the
‘‘General requirements.’’ Under that Safety. airplane and do all applicable on-condition
section, Congress charges the FAA with actions using a method approved in
The Proposed Amendment accordance with the procedures specified in
promoting safe flight of civil aircraft in
air commerce by prescribing regulations Accordingly, under the authority paragraph (j) of this AD.
for practices, methods, and procedures delegated to me by the Administrator, (h) Required Actions for Groups 2
the Administrator finds necessary for the FAA proposes to amend 14 CFR part Through 5
safety in air commerce. This regulation 39 as follows: Except as specified in paragraph (i) of this
is within the scope of that authority AD: For airplanes identified as Groups 2
because it addresses an unsafe condition PART 39—AIRWORTHINESS through 5 in Boeing Requirements Bulletin
that is likely to exist or develop on DIRECTIVES 737–53A1375 RB, dated March 12, 2018, at
products identified in this rulemaking the applicable times specified in the
■ 1. The authority citation for part 39 ‘‘Compliance’’ paragraph of Boeing
action. continues to read as follows:
This proposed AD is issued in Requirements Bulletin 737–53A1375 RB,
Authority: 49 U.S.C. 106(g), 40113, 44701. dated March 12, 2018, do all applicable
accordance with authority delegated by actions identified in, and in accordance with,
the Executive Director, Aircraft § 39.13 [Amended] the Accomplishment Instructions of Boeing
Certification Service, as authorized by ■ 2. The FAA amends § 39.13 by adding Requirements Bulletin 737–53A1375 RB,
FAA Order 8000.51C. In accordance the following new airworthiness dated March 12, 2018.
with that order, issuance of ADs is directive (AD): Note 1 to paragraph (h) of this AD:
normally a function of the Compliance Guidance for accomplishing the actions
and Airworthiness Division, but during The Boeing Company: Docket No. FAA– required by this AD can be found in Boeing
2018–0793; Product Identifier 2018– Alert Service Bulletin 737–53A1375, dated
this transition period, the Executive
NM–057–AD. March 12, 2018, which is referred to in
Director has delegated the authority to
issue ADs applicable to transport (a) Comments Due Date Boeing Requirements Bulletin 737–53A1375
RB, dated March 12, 2018.
category airplanes and associated We must receive comments by November
appliances to the Director of the System 1, 2018. (i) Exceptions to Service Information
Oversight Division. (b) Affected ADs Specifications
Regulatory Findings None. (1) For purposes of determining
compliance with the requirements of this AD:
We determined that this proposed AD (c) Applicability Where Boeing Requirements Bulletin 737–
would not have federalism implications This AD applies to all The Boeing 53A1375 RB, dated March 12, 2018, uses the
under Executive Order 13132. This Company Model 737–100, –200, –200C, phrase ‘‘the original issue date of
proposed AD would not have a –300, –400, and –500 series airplanes, Requirements Bulletin 737–53A1375 RB,’’
daltland on DSKBBV9HB2PROD with PROPOSALS
substantial direct effect on the States, on certificated in any category. this AD requires using ‘‘the effective date of
the relationship between the national this AD.’’
(d) Subject (2) Where Boeing Requirements Bulletin
Government and the States, or on the 737–53A1375 RB, dated March 12, 2018,
Air Transport Association (ATA) of
distribution of power and America Code 53, Fuselage. specifies contacting Boeing for repair
responsibilities among the various instructions, this AD requires repair using a
levels of government. (e) Unsafe Condition method approved in accordance with the
For the reasons discussed above, I This AD was prompted by a report of procedures specified in paragraph (j) of this
certify this proposed regulation: cracks in the body station (STA) 303.9 frame AD.
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(j) Alternative Methods of Compliance DEPARTMENT OF TRANSPORTATION • Hand Delivery: Deliver to Mail
(AMOCs) address above between 9 a.m. and 5
(1) The Manager, Los Angeles ACO Branch, Federal Aviation Administration p.m., Monday through Friday, except
FAA, has the authority to approve AMOCs Federal holidays.
for this AD, if requested using the procedures 14 CFR Part 39 For service information identified in
found in 14 CFR 39.19. In accordance with [Docket No. FAA–2018–0795; Product
this NPRM, contact Airbus SAS,
14 CFR 39.19, send your request to your Identifier 2018–NM–076–AD] Airworthiness Office—EIAS, Rond-
principal inspector or local Flight Standards Point Emile Dewoitine No: 2, 31700
District Office, as appropriate. If sending RIN 2120–AA64 Blagnac Cedex, France; phone: +33 5 61
information directly to the manager of the 93 36 96; fax: +33 5 61 93 44 51; email:
Airworthiness Directives; Airbus SAS account.airworth-eas@airbus.com;
certification office, send it to the attention of
Airplanes internet: http://www.airbus.com. You
the person identified in paragraph (k)(1) of
this AD. Information may be emailed to: AGENCY: Federal Aviation may view this referenced service
9-ANM-LAACO-AMOC-Requests@faa.gov. Administration (FAA), DOT. information at the FAA, Transport
(2) Before using any approved AMOC, ACTION: Notice of proposed rulemaking Standards Branch, 2200 South 216th St.,
notify your appropriate principal inspector, (NPRM). Des Moines, WA. For information on the
or lacking a principal inspector, the manager availability of this material at the FAA,
of the local flight standards district office/ We propose to supersede
SUMMARY: call 206–231–3195.
certificate holding district office. Airworthiness Directive (AD) 2014–20–
04, which applies to all Airbus SAS Examining the AD Docket
(3) An AMOC that provides an acceptable
level of safety may be used for any repair, Model A318 series airplanes; Airbus You may examine the AD docket on
modification, or alteration required by this SAS Model A319 series airplanes; the internet at http://
AD if it is approved by the Boeing Airbus SAS Model A320–111, –211, www.regulations.gov by searching for
Commercial Airplanes Organization –212, –214, –231, –232, and –233 and locating Docket No. FAA–2018–
Designation Authorization (ODA) that has airplanes; and Airbus SAS Model A321– 0795; or in person at Docket Operations
been authorized by the Manager, Los Angeles 111, –112, –131, –211, –212, –213, –231, between 9 a.m. and 5 p.m., Monday
ACO Branch, FAA, to make those findings. and –232 airplanes. AD 2014–20–04 through Friday, except Federal holidays.
To be approved, the repair method, requires repetitive inspections for The AD docket contains this NPRM, the
modification deviation, or alteration cracking of the four titanium angles regulatory evaluation, any comments
deviation must meet the certification basis ofbetween the belly fairing and the keel received, and other information. The
the airplane, and the approval must beam side panel, an inspection for street address for Docket Operations
specifically refer to this AD. cracking of the open holes if any (phone: 800–647–5527) is in the
cracking is found in the titanium angles, ADDRESSES section. Comments will be
(k) Related Information
and repair or replacement if necessary. available in the AD docket shortly after
(1) For more information about this AD, Since we issued AD 2014–20–04, we receipt.
contact Galib Abumeri, Aerospace Engineer, have determined that additional work is FOR FURTHER INFORMATION CONTACT:
Airframe Section, FAA, Los Angeles ACO necessary for certain airplanes. This Sanjay Ralhan, Aerospace Engineer,
Branch, 3960 Paramount Boulevard, proposed AD would continue to require International Section, Transport
Lakewood, CA 90712–4137; phone: 562–627– repetitive inspections for cracking of the Standards Branch, FAA, 2200 South
5324; fax: 562–627–5210; email: four titanium angles between the belly 216th St., Des Moines, WA 98198;
galib.abumeri@faa.gov. fairing and the keel beam side panel, an phone and fax 206–231–3223.
(2) For service information identified in inspection for cracking of the open SUPPLEMENTARY INFORMATION:
this AD, contact Boeing Commercial holes if any cracking is found in the
Airplanes, Attention: Contractual & Data titanium angles, and repair or Comments Invited
Services (C&DS), 2600 Westminster Blvd., replacement if necessary. This proposed We invite you to send any written
MC 110–SK57, Seal Beach, CA 90740–5600; AD would also revise the applicability relevant data, views, or arguments about
phone: 562–797–1717; internet: https:// by adding Model A320–216 airplanes. this proposal. Send your comments to
www.myboeingfleet.com. You may view this This proposed AD would also require a an address listed under the ADDRESSES
referenced service information at the FAA, detailed inspection for and replacement section. Include ‘‘Docket No. FAA–
Transport Standards Branch, 2200 South of certain rivets (including a rotating 2018–0795; Product Identifier 2018–
216th St., Des Moines, WA. For information probe test for cracks in the open holes), NM–076–AD’’ at the beginning of your
on the availability of this material at the and corrective actions if necessary. We comments. We specifically invite
FAA, call 206–231–3195. are proposing this AD to address the comments on the overall regulatory,
Issued in Des Moines, Washington, on unsafe condition on these products. economic, environmental, and energy
August 30, 2018. DATES: We must receive comments on aspects of this proposed AD. We will
Jeffrey E. Duven, this proposed AD by November 1, 2018. consider all comments received by the
Director, System Oversight Division, Aircraft ADDRESSES: You may send comments, closing date and may amend this
Certification Service. using the procedures found in 14 CFR proposed AD based on those comments.
[FR Doc. 2018–19840 Filed 9–14–18; 8:45 am] 11.43 and 11.45, by any of the following We will post all comments we
methods: receive, without change, to http://
BILLING CODE 4910–13–P
• Federal eRulemaking Portal: Go to www.regulations.gov, including any
daltland on DSKBBV9HB2PROD with PROPOSALS
http://www.regulations.gov. Follow the personal information you provide. We
instructions for submitting comments. will also post a report summarizing each
• Fax: 202–493–2251. substantive verbal contact we receive
• Mail: U.S. Department of about this proposed AD.
Transportation, Docket Operations,
M–30, West Building Ground Floor, Discussion
Room W12–140, 1200 New Jersey We issued AD 2014–20–04,
Avenue SE, Washington, DC 20590. Amendment 39–17977 (79 FR 59636,
VerDate Sep<11>2014 16:40 Sep 14, 2018 Jkt 244001 PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 E:\FR\FM\17SEP1.SGM 17SEP1](https://thefederalregister.org/doc/83_FR_47082/page/4.svg)
Document Created: 2018-09-15 01:38:12
Document Modified: 2018-09-15 01:38:12
| 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 November 1, 2018. | |
| Contact | Galib Abumeri, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562-627- 5210; email: [email protected] | |
| FR Citation | 83 FR 46902 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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