80 FR 74726 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 229 (November 30, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 229 (November 30, 2015)
| Page Range | 74726-74729 | |
| FR Document | 2015-30223 |
[Federal Register Volume 80, Number 229 (Monday, November 30, 2015)] [Proposed Rules] [Pages 74726-74729] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-30223] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-6541; Directorate Identifier 2015-NM-135-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 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This proposed AD was prompted by reports of a manufacturing oversight, in which a supplier omitted the required protective finish on certain bushings installed in the rear spar upper chord on horizontal stabilizers, which could lead to galvanic corrosion and consequent cracking of the rear spar upper chord. This proposed AD would require an inspection or records check to determine if affected horizontal stabilizers are installed, related investigative actions, and for affected horizontal stabilizers, repetitive inspections for any crack of the horizontal stabilizer rear spar upper chord, and corrective action if necessary. We are proposing this AD to detect and correct cracking of the rear spar upper chord, which can result in the failure of the upper chord and consequent departure of the horizontal stabilizer from the airplane, which can lead to loss of continued safe flight and landing. DATES: We must receive comments on this proposed AD by January 14, 2016. 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 proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-544- 5000, extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 6541. 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-2015- 6541; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Jason Deutschman, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6595; fax: 425-917-6590; 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-2015-6541; Directorate Identifier 2015-NM-135-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD 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 received reports of a manufacturing oversight, in which the required protective finish (zinc-nickel alloy plate or cadmium plate) was omitted on the 182A1508-4/-5/-6 bushings (in line with the terminal fitting holes) installed in the rear spar upper chord on horizontal stabilizers with certain serial numbers. This issue was discovered after production of the affected stabilizers. The 182A1508-4/-5/-6 bushings are made from aluminum-nickel-bronze. Installing these bushings, without the required protective finish, into the 2024-T3511 aluminum horizontal stabilizer rear spar upper chord can lead to galvanic corrosion between the dissimilar metals. Bushings with galvanic corrosion, if not corrected, can lead to cracking of the rear spar upper chord, which can result in the failure of the upper chord and consequent departure of the horizontal stabilizer from the airplane, which can lead to loss of continued safe flight and landing. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737-55A1097, dated July 1, 2015. The service information describes procedures for an inspection or records review to determine if affected horizontal stabilizers are installed, [[Page 74727]] related investigative actions, high frequency eddy current inspections for any crack of the horizontal stabilizer rear spar upper chord, and corrective action if necessary. 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 of this NPRM. 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 accomplishing the actions specified in the service information described previously, except as discussed under ``Differences Between this Proposed AD and the Service Information.'' 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'' are actions that correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 737-55A1097, dated July 1, 2015, specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions 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. Explanation of ``RC'' Steps in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for annotating which steps in the service information are required for compliance with an AD. Differentiating these steps from other tasks in the service information is expected to improve an owner's/operator's understanding of crucial AD requirements and help provide consistent judgment in AD compliance. The steps identified as Required for Compliance (RC) in any service information identified previously have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. For service information that contains steps that are labeled as RC, the following provisions apply: (1) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD, and an AMOC is required for any deviations to RC steps, including substeps and identified figures; and (2) steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. Costs of Compliance We estimate that this proposed AD affects 1,397 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Inspection or check................... 1 work-hour x $85 per $0 $85 $118,745 hour = $85. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary inspections that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need these inspections: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Inspections................................... 4 work-hours x $85 per hour = $0 $340 $340. ---------------------------------------------------------------------------------------------------------------- According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. We have received no definitive data that would enable us to provide cost estimates for the on-condition repairs 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. [[Page 74728]] 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-2015-6541; Directorate Identifier 2015-NM-135-AD. (a) Comments Due Date We must receive comments by January 14, 2016. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 737-600, -700, - 700C, -800, -900, and 900ER series airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 55, Stabilizers. (e) Unsafe Condition This AD was prompted by reports of a manufacturing oversight, in which a supplier omitted the required protective finish on certain bushings installed in the rear spar upper chord on horizontal stabilizers, which could lead to galvanic corrosion and consequent cracking of the rear spar upper chord. We are issuing this AD to detect and correct cracking of the rear spar upper chord, which can result in the failure of the upper chord and consequent departure of the horizontal stabilizer from the airplane, which can lead to loss of continued safe flight and landing. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Serial Number Check or Inspection To Determine If Certain Horizontal Stabilizers Are Installed, Related Investigative Actions, Repetitive Inspections for Cracks, and Corrective Action (1) Except as specified in paragraph (h)(1) of this AD, within the compliance time identified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1097, dated July 1, 2015, do the actions specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD. (i) Do a records check to determine if an affected horizontal stabilizer is installed and if any horizontal stabilizer has been exchanged, and do all applicable related investigative actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-55A1097, dated July 1, 2015. Affected horizontal stabilizers are identified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737-55A1097, dated July 1, 2015. (ii) Do an inspection of the horizontal stabilizer identification plate to determine if any affected horizontal stabilizer is installed, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-55A1097, dated July 1, 2015. Affected horizontal stabilizers are identified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 55A1097, dated July 1, 2015. (2) If, during any action required by paragraph (g)(1)(i) or (g)(1)(ii) of this AD, any affected horizontal stabilizer is found: Except as specified in paragraph (h)(1) of this AD, within the compliance time identified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1097, dated July 1, 2015, do a high frequency eddy current (HFEC) inspection for any crack of the horizontal stabilizer rear spar upper chord and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-55A1097, dated July 1, 2015, except as required by paragraph (h)(2) of this AD. Repeat the inspection thereafter at intervals identified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1097, dated July 1, 2015. (h) Exceptions to the Service Information Specifications (1) Where Boeing Alert Service Bulletin 737-55A1097, dated July 1, 2015, specifies a compliance time ``after the original issue date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) If any cracking is found during any inspection required by this AD, and Boeing Alert Service Bulletin 737-55A1097, dated July 1, 2015, specifies to contact Boeing for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (i) Parts Installation Prohibition As of the effective date of this AD, no person may install a horizontal stabilizer on any airplane, except as specified in paragraphs (i)(1) and (i)(2) of this AD. (1) A horizontal stabilizer may be installed if the part is inspected in accordance with ``Part 2: Horizontal Stabilizer Identification Plate Inspection'' of the Accomplishments Instructions of Boeing Alert Service Bulletin 737-55A1097, dated July 1, 2015, and no affected serial number is found. (2) A horizontal stabilizer may be installed if the part is inspected in accordance with ``Part 2: Horizontal Stabilizer Identification Plate Inspection'' of the Accomplishments Instructions of Boeing Alert Service Bulletin 737-55A1097, dated July 1, 2015, and an affected serial number is found, provided the actions specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD are done, as applicable. (i) An initial HFEC inspection specified in paragraph (g)(2) of this AD is done before further flight and thereafter repetitive HFEC inspections specified in paragraph (g)(2) of this AD are done within the compliance times specified in paragraph (g)(2) of this AD. (ii) All applicable corrective actions are done before further flight as required by paragraph (h)(2) of this AD. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), 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 ACO, send it to the attention of the person identified in paragraph (k) 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 required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet [[Page 74729]] the certification basis of the airplane, and the approval must specifically refer to this AD. (4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (j)(4)(i) and (j)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (k) Related Information (1) For more information about this AD, contact Jason Deutschman, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6595; fax: 425-917-6590; email: [email protected]. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206- 544-5000, extension 1; fax: 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on November 20, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-30223 Filed 11-27-15; 8:45 am] BILLING CODE 4910-13-P
![74726 Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules
(l) Special Flight Permits inspections for any crack of the Airframe Branch, ANM–120S, FAA,
Special flight permits, as described in horizontal stabilizer rear spar upper Seattle Aircraft Certification Office
Section 21.197 and Section 21.199 of the chord, and corrective action if (ACO), 1601 Lind Avenue SW., Renton,
Federal Aviation Regulations (14 CFR 21.197 necessary. We are proposing this AD to WA 98057–3356; phone: 425–917–6595;
and 21.199), are not allowed. detect and correct cracking of the rear fax: 425–917–6590; email:
(m) Related Information spar upper chord, which can result in jason.deutschman@faa.gov.
(1) Refer to Mandatory Continuing the failure of the upper chord and SUPPLEMENTARY INFORMATION:
Airworthiness Information (MCAI) EASA consequent departure of the horizontal
stabilizer from the airplane, which can Comments Invited
Airworthiness Directive 2015–0038, dated
March 4, 2015, for related information. This lead to loss of continued safe flight and We invite you to send any written
MCAI may be found in the AD docket on the landing. relevant data, views, or arguments about
Internet at http://www.regulations.gov by DATES: We must receive comments on this proposal. Send your comments to
searching for and locating Docket No. FAA– an address listed under the ADDRESSES
2015–6539.
this proposed AD by January 14, 2016.
section. Include ‘‘Docket No. FAA–
(2) For service information identified in ADDRESSES: You may send comments,
2015–6541; Directorate Identifier 2015–
this AD contact Airbus, Airworthiness using the procedures found in 14 CFR
Office—EIAS, 1 Rond Point Maurice
NM–135–AD’’ at the beginning of your
11.43 and 11.45, by any of the following
Bellonte, 31707 Blagnac Cedex, France; comments. We specifically invite
methods:
comments on the overall regulatory,
telephone +33 5 61 93 36 96; fax +33 5 61 • Federal eRulemaking Portal: Go to
93 44 51; email account.airworth-eas@ economic, environmental, and energy
http://www.regulations.gov. Follow the
airbus.com; Internet http://www.airbus.com. aspects of this proposed AD. We will
You may view this service information at the
instructions for submitting comments.
consider all comments received by the
FAA, Transport Airplane Directorate, 1601 • Fax: 202–493–2251.
closing date and may amend this
Lind Avenue SW., Renton, WA. For • Mail: U.S. Department of
proposed AD because of those
information on the availability of this Transportation, Docket Operations, M–
comments.
material at the FAA, call 425–227–1221. 30, West Building Ground Floor, Room
We will post all comments we
Issued in Renton, Washington, on W12–140, 1200 New Jersey Avenue SE.,
receive, without change, to http://
November 20, 2015. Washington, DC 20590.
www.regulations.gov, including any
Jeffrey E. Duven, • Hand Delivery: Deliver to Mail
personal information you provide. We
Manager, Transport Airplane Directorate,
address above between 9 a.m. and 5
will also post a report summarizing each
Aircraft Certification Service. p.m., Monday through Friday, except
substantive verbal contact we receive
Federal holidays.
[FR Doc. 2015–30216 Filed 11–27–15; 8:45 am] about this proposed AD.
For service information identified in
BILLING CODE 4910–13–P
this proposed AD, contact Boeing Discussion
Commercial Airplanes, Attention: Data We received reports of a
DEPARTMENT OF TRANSPORTATION & Services Management, P.O. Box 3707, manufacturing oversight, in which the
MC 2H–65, Seattle, WA 98124–2207; required protective finish (zinc-nickel
Federal Aviation Administration telephone: 206–544–5000, extension 1; alloy plate or cadmium plate) was
fax: 206–766–5680; Internet: https:// omitted on the 182A1508–4/–5/–6
14 CFR Part 39 www.myboeingfleet.com. You may view bushings (in line with the terminal
this referenced service information at fitting holes) installed in the rear spar
[Docket No. FAA–2015–6541; Directorate the FAA, Transport Airplane
Identifier 2015–NM–135–AD] upper chord on horizontal stabilizers
Directorate, 1601 Lind Avenue SW., with certain serial numbers. This issue
RIN 2120–AA64 Renton, WA. For information on the was discovered after production of the
availability of this material at the FAA, affected stabilizers.
Airworthiness Directives; The Boeing call 425–227–1221. It is also available The 182A1508–4/–5/–6 bushings are
Company Airplanes on the Internet at http:// made from aluminum-nickel-bronze.
AGENCY: Federal Aviation www.regulations.gov by searching for Installing these bushings, without the
Administration (FAA), DOT. and locating Docket No. FAA–2015– required protective finish, into the
ACTION: Notice of proposed rulemaking
6541. 2024–T3511 aluminum horizontal
(NPRM). Examining the AD Docket stabilizer rear spar upper chord can lead
to galvanic corrosion between the
SUMMARY: We propose to adopt a new You may examine the AD docket on dissimilar metals. Bushings with
airworthiness directive (AD) for all The the Internet at http:// galvanic corrosion, if not corrected, can
Boeing Company Model 737–600, –700, www.regulations.gov by searching for lead to cracking of the rear spar upper
–700C, –800, –900, and –900ER series and locating Docket No. FAA–2015– chord, which can result in the failure of
airplanes. This proposed AD was 6541; or in person at the Docket the upper chord and consequent
prompted by reports of a manufacturing Management Facility between 9 a.m. departure of the horizontal stabilizer
oversight, in which a supplier omitted and 5 p.m., Monday through Friday, from the airplane, which can lead to
the required protective finish on certain except Federal holidays. The AD docket loss of continued safe flight and
bushings installed in the rear spar upper contains this proposed AD, the landing.
chord on horizontal stabilizers, which regulatory evaluation, any comments
jstallworth on DSK7TPTVN1PROD with PROPOSALS
could lead to galvanic corrosion and received, and other information. The Related Service Information Under 1
consequent cracking of the rear spar street address for the Docket Office CFR Part 51
upper chord. This proposed AD would (phone: 800–647–5527) is in the We reviewed Boeing Alert Service
require an inspection or records check ADDRESSES section. Comments will be Bulletin 737–55A1097, dated July 1,
to determine if affected horizontal available in the AD docket shortly after 2015. The service information describes
stabilizers are installed, related receipt. procedures for an inspection or records
investigative actions, and for affected FOR FURTHER INFORMATION CONTACT: review to determine if affected
horizontal stabilizers, repetitive Jason Deutschman, Aerospace Engineer, horizontal stabilizers are installed,
VerDate Sep<11>2014 15:18 Nov 27, 2015 Jkt 238001 PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 E:\FR\FM\30NOP1.SGM 30NOP1](https://thefederalregister.org/doc/80_FR_74955/page/1.svg)
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Regulatory Findings (e) Unsafe Condition (h) Exceptions to the Service Information
This AD was prompted by reports of a Specifications
We determined that this proposed AD
manufacturing oversight, in which a supplier (1) Where Boeing Alert Service Bulletin
would not have federalism implications 737–55A1097, dated July 1, 2015, specifies a
omitted the required protective finish on
under Executive Order 13132. This certain bushings installed in the rear spar compliance time ‘‘after the original issue date
proposed AD would not have a upper chord on horizontal stabilizers, which of this service bulletin,’’ this AD requires
substantial direct effect on the States, on could lead to galvanic corrosion and compliance within the specified compliance
the relationship between the national consequent cracking of the rear spar upper time after the effective date of this AD.
Government and the States, or on the chord. We are issuing this AD to detect and (2) If any cracking is found during any
distribution of power and inspection required by this AD, and Boeing
correct cracking of the rear spar upper chord,
Alert Service Bulletin 737–55A1097, dated
responsibilities among the various which can result in the failure of the upper
July 1, 2015, specifies to contact Boeing for
levels of government. chord and consequent departure of the appropriate action: Before further flight,
For the reasons discussed above, I horizontal stabilizer from the airplane, which repair using a method approved in
certify this proposed regulation: can lead to loss of continued safe flight and accordance with the procedures specified in
landing. paragraph (j) of this AD.
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866, (f) Compliance (i) Parts Installation Prohibition
(2) Is not a ‘‘significant rule’’ under Comply with this AD within the As of the effective date of this AD, no
the DOT Regulatory Policies and compliance times specified, unless already person may install a horizontal stabilizer on
Procedures (44 FR 11034, February 26, done. any airplane, except as specified in
1979), paragraphs (i)(1) and (i)(2) of this AD.
(g) Serial Number Check or Inspection To (1) A horizontal stabilizer may be installed
(3) Will not affect intrastate aviation Determine If Certain Horizontal Stabilizers if the part is inspected in accordance with
in Alaska, and Are Installed, Related Investigative Actions, ‘‘Part 2: Horizontal Stabilizer Identification
(4) Will not have a significant Repetitive Inspections for Cracks, and Plate Inspection’’ of the Accomplishments
economic impact, positive or negative, Corrective Action Instructions of Boeing Alert Service Bulletin
on a substantial number of small entities (1) Except as specified in paragraph (h)(1) 737–55A1097, dated July 1, 2015, and no
under the criteria of the Regulatory of this AD, within the compliance time affected serial number is found.
Flexibility Act. identified in paragraph 1.E., ‘‘Compliance,’’ (2) A horizontal stabilizer may be installed
of Boeing Alert Service Bulletin 737– if the part is inspected in accordance with
List of Subjects in 14 CFR Part 39 55A1097, dated July 1, 2015, do the actions ‘‘Part 2: Horizontal Stabilizer Identification
specified in paragraph (g)(1)(i) or (g)(1)(ii) of Plate Inspection’’ of the Accomplishments
Air transportation, Aircraft, Aviation Instructions of Boeing Alert Service Bulletin
safety, Incorporation by reference, this AD.
(i) Do a records check to determine if an 737–55A1097, dated July 1, 2015, and an
Safety. affected serial number is found, provided the
affected horizontal stabilizer is installed and
actions specified in paragraphs (i)(2)(i) and
The Proposed Amendment if any horizontal stabilizer has been
(i)(2)(ii) of this AD are done, as applicable.
exchanged, and do all applicable related (i) An initial HFEC inspection specified in
Accordingly, under the authority investigative actions, in accordance with the
delegated to me by the Administrator, paragraph (g)(2) of this AD is done before
Accomplishment Instructions of Boeing Alert further flight and thereafter repetitive HFEC
the FAA proposes to amend 14 CFR part Service Bulletin 737–55A1097, dated July 1, inspections specified in paragraph (g)(2) of
39 as follows: 2015. Affected horizontal stabilizers are this AD are done within the compliance
identified in the Accomplishment times specified in paragraph (g)(2) of this AD.
PART 39—AIRWORTHINESS Instructions of Boeing Alert Service Bulletin (ii) All applicable corrective actions are
DIRECTIVES 737–55A1097, dated July 1, 2015. done before further flight as required by
(ii) Do an inspection of the horizontal paragraph (h)(2) of this AD.
■ 1. The authority citation for part 39 stabilizer identification plate to determine if
continues to read as follows: (j) Alternative Methods of Compliance
any affected horizontal stabilizer is installed,
(AMOCs)
Authority: 49 U.S.C. 106(g), 40113, 44701. in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin (1) The Manager, Seattle Aircraft
§ 39.13 [Amended] 737–55A1097, dated July 1, 2015. Affected Certification Office (ACO), FAA, has the
horizontal stabilizers are identified in the authority to approve AMOCs for this AD, if
■ 2. The FAA amends § 39.13 by adding requested using the procedures found in 14
Accomplishment Instructions of Boeing Alert
the following new airworthiness Service Bulletin 737–55A1097, dated July 1, CFR 39.19. In accordance with 14 CFR 39.19,
directive (AD): 2015. send your request to your principal inspector
(2) If, during any action required by or local Flight Standards District Office, as
The Boeing Company: Docket No. FAA–
paragraph (g)(1)(i) or (g)(1)(ii) of this AD, any appropriate. If sending information directly
2015–6541; Directorate Identifier 2015–
to the manager of the ACO, send it to the
NM–135–AD. affected horizontal stabilizer is found: Except
attention of the person identified in
as specified in paragraph (h)(1) of this AD,
(a) Comments Due Date paragraph (k) of this AD. Information may be
within the compliance time identified in
We must receive comments by January 14, emailed to: 9-ANM-Seattle-ACO-AMOC-
paragraph 1.E., ‘‘Compliance,’’ of Boeing Requests@faa.gov.
2016. Alert Service Bulletin 737–55A1097, dated (2) Before using any approved AMOC,
(b) Affected ADs July 1, 2015, do a high frequency eddy notify your appropriate principal inspector,
current (HFEC) inspection for any crack of or lacking a principal inspector, the manager
None.
the horizontal stabilizer rear spar upper of the local flight standards district office/
jstallworth on DSK7TPTVN1PROD with PROPOSALS
(c) Applicability chord and do all applicable corrective certificate holding district office.
This AD applies to all The Boeing actions, in accordance with the (3) An AMOC that provides an acceptable
Company Model 737–600, –700, –700C, Accomplishment Instructions of Boeing Alert level of safety may be used for any repair
–800, –900, and 900ER series airplanes, Service Bulletin 737–55A1097, dated July 1, required by this AD if it is approved by the
certificated in any category. 2015, except as required by paragraph (h)(2) Boeing Commercial Airplanes Organization
of this AD. Repeat the inspection thereafter Designation Authorization (ODA) that has
(d) Subject at intervals identified in paragraph 1.E., been authorized by the Manager, Seattle
Air Transport Association (ATA) of ‘‘Compliance,’’ of Boeing Alert Service ACO, to make those findings. For a repair
America Code 55, Stabilizers. Bulletin 737–55A1097, dated July 1, 2015. method to be approved, the repair must meet
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![Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules 74729
the certification basis of the airplane, and the AD was prompted by reports of cracking FOR FURTHER INFORMATION CONTACT:
approval must specifically refer to this AD. of the aft fixed fairing (AFF) of the Sanjay Ralhan, Aerospace Engineer,
(4) For service information that contains pylons due to fatigue damage of the International Branch, ANM–116,
steps that are labeled as Required for structure. This proposed AD would Transport Airplane Directorate, FAA,
Compliance (RC), the provisions of
paragraphs (j)(4)(i) and (j)(4)(ii) of this AD
require repetitive inspections for 1601 Lind Avenue SW., Renton, WA
apply. damage and cracking of the AFF of the 98057–3356; telephone 425–227–1405;
(i) The steps labeled as RC, including pylons, and repair if necessary. We are fax 425–227–1149.
substeps under an RC step and any figures proposing this AD to detect and correct SUPPLEMENTARY INFORMATION:
identified in an RC step, must be done to damage and cracking of the AFF of the
comply with the AD. An AMOC is required pylons, which could result in Comments Invited
for any deviations to RC steps, including detachment of a pylon and consequent
substeps and identified figures. We invite you to send any written
reduced structural integrity of the relevant data, views, or arguments about
(ii) Steps not labeled as RC may be airplane.
deviated from using accepted methods in this proposed AD. Send your comments
accordance with the operator’s maintenance DATES: We must receive comments on to an address listed under the
or inspection program without obtaining this proposed AD by January 14, 2016. ADDRESSES section. Include ‘‘Docket No.
approval of an AMOC, provided the RC steps, FAA–2015–6537; Directorate Identifier
including substeps and identified figures, can ADDRESSES: You may send comments,
2014–NM–154–AD’’ at the beginning of
still be done as specified, and the airplane using the procedures found in 14 CFR
your comments. We specifically invite
can be put back in an airworthy condition. 11.43 and 11.45, by any of the following
comments on the overall regulatory,
methods:
(k) Related Information economic, environmental, and energy
• Federal eRulemaking Portal: Go to aspects of this proposed AD. We will
(1) For more information about this AD, http://www.regulations.gov. Follow the
contact Jason Deutschman, Aerospace consider all comments received by the
Engineer, Airframe Branch, ANM–120S,
instructions for submitting comments. closing date and may amend this
FAA, Seattle ACO, 1601 Lind Avenue SW., • Fax: (202) 493–2251. proposed AD based on those comments.
Renton, WA 98057–3356; phone: 425–917– • Mail: U.S. Department of We will post all comments we
6595; fax: 425–917–6590; email: Transportation, Docket Operations, M– receive, without change, to http://
jason.deutschman@faa.gov. 30, West Building Ground Floor, Room
(2) For service information identified in
www.regulations.gov, including any
W12–140, 1200 New Jersey Avenue SE., personal information you provide. We
this AD, contact Boeing Commercial Washington, DC 20590.
Airplanes, Attention: Data & Services will also post a report summarizing each
Management, P. O. Box 3707, MC 2H–65, • Hand Delivery: U.S. Department of substantive verbal contact we receive
Seattle, WA 98124–2207; telephone: 206– Transportation, Docket Operations, M– about this proposed AD.
544–5000, extension 1; fax: 206–766–5680; 30, West Building Ground Floor, Room
Internet https://www.myboeingfleet.com. You W12–140, 1200 New Jersey Avenue SE., Discussion
may view this referenced service information Washington, DC, between 9 a.m. and 5 The European Aviation Safety Agency
at the FAA, Transport Airplane Directorate, p.m., Monday through Friday, except (EASA), which is the Technical Agent
1601 Lind Avenue SW., Renton, WA. For Federal holidays.
information on the availability of this
for the Member States of the European
For service information identified in Union, has issued EASA Airworthiness
material at the FAA, call 425–227–1221.
this proposed AD, contact Airbus, Directive 2014–0154, dated July 2, 2014
Issued in Renton, Washington, on Airworthiness Office—EAS, 1 Rond (referred to after this as the Mandatory
November 20, 2015. Point Maurice Bellonte, 31707 Blagnac Continuing Airworthiness Information,
Jeffrey E. Duven, Cedex, France; telephone +33 5 61 93 36 or ‘‘the MCAI’’), to correct an unsafe
Manager, Transport Airplane Directorate, 96; fax +33 5 61 93 44 51; email condition for certain Airbus Model
Aircraft Certification Service. account.airworth-eas@airbus.com; A318, A319, A320, and A321 series
[FR Doc. 2015–30223 Filed 11–27–15; 8:45 am] Internet http://www.airbus.com. You airplanes. The MCAI states:
BILLING CODE 4910–13–P may view this referenced service
On aeroplanes equipped with post-mod
information at the FAA, Transport 33844 CFM pylons, several operators have
Airplane Directorate, 1601 Lind Avenue reported cracks on the Aft Fixed Fairing
DEPARTMENT OF TRANSPORTATION SW., Renton, WA. For information on (AFF). After material analysis, it appears that
the availability of this material at the the pylon AFF structure, especially on this
Federal Aviation Administration FAA, call 425–227–1221. configuration, is subject to fatigue constraint
damage which could lead to pylon AFF
14 CFR Part 39 Examining the AD Docket cracks.
You may examine the AD docket on Further to these findings, Airbus released
[Docket No. FAA–2015–6537; Directorate Alert Operators Transmission (AOT)
Identifier 2014–NM–154–AD] the Internet at http://
A54N002–12 which provides instructions to
www.regulations.gov by searching for inspect the pylon AFF, applicable only to
RIN 2120–AA64 and locating Docket No. FAA–2015– aeroplanes incorporating Airbus production
6537; or in person at the Docket mod 33844 on CFM pylons. More recently,
Airworthiness Directives; Airbus
Management Facility between 9 a.m. Airbus issued Service Bulletin (SB) A320–
Airplanes
and 5 p.m., Monday through Friday, 54–1027, superseding AOT A54N002–12.
AGENCY: Federal Aviation except Federal holidays. The AD docket This condition, if not detected and
jstallworth on DSK7TPTVN1PROD with PROPOSALS
Administration (FAA), DOT. contains this proposed AD, the corrected, could lead to detachment of a
regulatory evaluation, any comments pylon AFF from the aeroplane, possibly
ACTION: Notice of proposed rulemaking resulting in injuries to persons on the
(NPRM). received, and other information. The
ground.
street address for the Docket Operations For the reasons described above, this
SUMMARY: We propose to adopt a new office (telephone (800) 647–5527) is in [EASA] AD requires repetitive detailed
airworthiness directive (AD) for certain the ADDRESSES section. Comments will inspections (DET) of the pylon AFF and,
Airbus Model A318, A319, A320, and be available in the AD docket shortly depending on findings, accomplishment of
A321 series airplanes. This proposed after receipt. applicable corrective action(s).
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Document Created: 2018-03-01 11:12:45
Document Modified: 2018-03-01 11:12:45
| 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 January 14, 2016. | |
| Contact | Jason Deutschman, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6595; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 80 FR 74726 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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