82 FR 15284 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 58 (March 28, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 58 (March 28, 2017)
| Page Range | 15284-15287 | |
| FR Document | 2017-05768 |
[Federal Register Volume 82, Number 58 (Tuesday, March 28, 2017)] [Rules and Regulations] [Pages 15284-15287] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-05768] [[Page 15284]] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9068; Directorate Identifier 2016-NM-067-AD; Amendment 39-18838; AD 2017-06-14] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. This AD was prompted by reports of cracks in the horizontal stabilizer lower skins. This AD requires inspections for cracking of the horizontal stabilizer lower skin, and corrective actions if necessary; and also provides actions that would terminate certain repetitive inspections. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective May 2, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 2, 2017. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, 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-2016- 9068. 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-2016- 9068; 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800-647- 5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: George Garrido, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5232; fax: 562-627-5210; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain The Boeing Company Model 737-300, -400, and -500 series airplanes. The NPRM published in the Federal Register on September 8, 2016 (81 FR 62022) (``the NPRM''). The NPRM was prompted by reports of cracks in the horizontal stabilizer lower skins. The NPRM proposed to require inspections for cracking of the horizontal stabilizer lower skin, including repetitive inspections, as applicable, and corrective actions if necessary; and also proposed actions that would terminate certain repetitive inspections. We are issuing this AD to detect and correct cracks in horizontal stabilizer lower skins resulting in reduced local stiffness of the horizontal stabilizer, which can cause heavy vibration leading to loss of structural integrity of the horizontal stabilizer. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Support for the NPRM Boeing expressed support for the NPRM. Request To Revise Repair Instructions All Nippon Airways (ANA) requested that we revise paragraphs (h)(1) and (h)(3) of the proposed AD to state ``repair common to the rear spar lower chord between station (STA) 83.50 and STA 249.10,'' instead of ``repair.'' ANA stated that there might be a repair installed on the lower skin of the horizontal stabilizer that is not addressed in Boeing Special Attention Service Bulletin 737-55-1059, Revision 1, dated April 6, 2016 (``SASB 737-55-1059 R1''). ANA explained that some structural repair manual repairs and external doublers are not applicable to the inspection area specified in SASB 737-55-1059 R1. We agree with ANA's request. Specifying the location of the applicable repairs may reduce potential confusion. Therefore, we have revised paragraphs (h)(1), (h)(2), and (h)(3) of this AD to specify the location of the applicable repairs. Request To Clarify Fastener Requirements ANA requested that we clarify the fastener requirements. ANA stated that figure 3 in Boeing Special Attention Service Bulletin 737-55-1059, dated September 10, 1998, specifies to use blind rivets and Hi-lok fasteners; however, compliance table 2, note (b), in SASB 737-55-1059 R1, states that doublers installed with solid rivets do not need to be inspected for any loose or missing fasteners. ANA explained that Boeing told ANA that Hi-lok fasteners do not require inspection for any loose or missing fasteners. We agree to clarify the fastener requirements. We infer that ANA is requesting that we update paragraph (h) of this AD to specify that Hi- lok fasteners do not require inspection. We have determined that Hi-lok fasteners do not require inspection. Therefore, we have added paragraph (i)(3) to this AD to specify that where SASB 737-55-1059 R1 specifies that doublers installed with solid rivets do not need to be inspected for loose or missing fasteners, this AD does not require doublers installed with solid rivets or Hi-lok fasteners to be inspected for loose or missing fasteners. We have also revised paragraph (h)(1) of this AD to reference this exception. Request To Revise Configuration Description ANA requested that we revise paragraph (h) of the proposed AD to refer to the horizontal stabilizer configuration with the applicable repair installed side only. ANA asserted that the wording of paragraph (h) of the proposed AD could be interpreted to require inspection of both the repaired and unrepaired sides of the horizontal stabilizer. We agree with ANA's request. The wording in the proposed AD is not clear regarding what is required if an airplane has left and right stabilizers that are different configurations. For example, the left- side stabilizer may have a repair installed common to the rear spar lower chord (configuration 2), whereas the right side may not have a repair (configuration 1). We have revised the affected airplanes in paragraph (g) of this AD from ``Group 1, Configuration 1, [[Page 15285]] airplanes'' to ``any Configuration 1 horizontal stabilizer on Group 1 airplanes''. We have revised the affected products in paragraph (h) of this AD from ``Group 1, Configuration 2, airplanes'' to ``any Configuration 2 horizontal stabilizer on Group 1 airplanes.'' Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that accomplishing the Supplemental Type Certificate (STC) ST01219SE does not affect the actions specified in the NPRM. We concur with the commenter. We have redesignated paragraph (c) of the proposed AD as paragraph (c)(1) of this AD and added paragraph (c)(2) to this AD to state that installation of STC ST01219SE does not affect the ability to accomplish the actions required by this final rule. Therefore, for airplanes on which STC ST01219SE is installed, a ``change in product'' AMOC approval request is not necessary to comply with the requirements of 14 CFR 39.17. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed SASB 737-55-1059 R1. The service information describes procedures for doing inspections of the horizontal stabilizer lower skin, and repairs. The service information also describes procedures for doing actions that would terminate certain repetitive inspections. 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. Costs of Compliance We estimate that this AD affects 270 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Parts Cost on U.S. Action Labor cost cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspection........................ 4 work-hours x $85 $0 $340 per inspection $91,800 per per hour = $340 per cycle. inspection cycle. inspection cycle. ---------------------------------------------------------------------------------------------------------------- Estimated Costs for Optional Actions ---------------------------------------------------------------------------------------------------------------- Parts Action Labor cost cost Cost per product ---------------------------------------------------------------------------------------------------------------- Modification............................. Up to 51 work-hours per $721 Up to $5,056 per stabilizer. stabilizer x $85 per hour = $4,335. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that will be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these repairs: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Parts Action Labor cost cost Cost per product ---------------------------------------------------------------------------------------------------------------- Skin splice repair....................... Up to 438 work-hours x $85 $0 Up to $37,230. per hour = $37,230. External doubler repair.................. 26 work-hours x $85 per hour 0 $2,210. = $2,210. ---------------------------------------------------------------------------------------------------------------- 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. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under 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. [[Page 15286]] Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2017-06-14 The Boeing Company: Amendment 39-18838; Docket No. FAA- 2016-9068; Directorate Identifier 2016-NM-067-AD. (a) Effective Date This AD is effective May 2, 2017. (b) Affected ADs None. (c) Applicability (1) This AD applies to The Boeing Company Model 737-300, -400, and -500 series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 737-55-1059, Revision 1, dated April 6, 2016 (``SASB 737-55-1059 R1''). (2) Installation of Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/ rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a ``change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. (d) Subject Air Transport Association (ATA) of America Code 55; Horizontal stabilizer. (e) Unsafe Condition This AD was prompted by reports of cracks in horizontal stabilizer lower skins. We are issuing this AD to detect and correct cracks in horizontal stabilizer lower skins, resulting in reduced local stiffness of the stabilizer, which can cause heavy vibration leading to loss of structural integrity of the horizontal stabilizer. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections, Related Investigative Actions, and Corrective Actions for Configuration 1 Horizontal Stabilizers on Group 1 Airplanes For any Configuration 1 horizontal stabilizer on Group 1 airplanes, as identified in SASB 737-55-1059 R1: Except as specified in paragraph (i)(1) of this AD, at the applicable time specified in paragraph 1.E., ``Compliance,'' of SASB 737-55-1059 R1, do a detailed inspection for cracking of the horizontal stabilizer lower skin; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of SASB 737-55-1059 R1, except as specified in paragraph (i)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection of the horizontal stabilizer lower skin, if applicable, thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of SASB 737- 55-1059 R1. Options specified in SASB 737-55-1059 R1 for accomplishing the inspections are acceptable for the corresponding requirements of this paragraph provided that the inspections are done at the applicable times in paragraph 1.E., ``Compliance,'' of the SASB 737-55-1059 R1. (h) Inspections, Related Investigative Actions, and Corrective Actions for Configuration 2 Horizontal Stabilizers on Group 1 Airplanes For any Configuration 2 horizontal stabilizer on Group 1 airplanes, as identified in SASB 737-55-1059 R1: Except as specified in paragraph (i)(1) of this AD, at the applicable time specified in paragraph 1.E., ``Compliance,'' of SASB 737-55-1059 R1, do the actions specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of SASB 737-55-1059 R1, except as specified in paragraph (i)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD, if applicable, thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of SASB 737-55-1059 R1. Options specified in SASB 737-55-1059 R1, for accomplishing the inspections are acceptable for the corresponding requirements of this paragraph provided that the inspections are done at the applicable times in paragraph 1.E., ``Compliance,'' of SASB 737-55-1059 R1. (1) Do a high frequency eddy current inspection for cracking of the skin around any repair common to the rear spar lower chord between station (STA) 83.50 and STA 249.10 which was done as specified in the structural repair manual or any external doubler repair, and a detailed inspection for any loose or any missing fastener of repaired doublers, except as specified in paragraph (i)(3) of this AD. (2) Do a detailed inspection for cracking of the inspar lower skin between STA 83.50 and STA 249.10, except in areas repaired common to the rear spar lower chord. (3) Do a low frequency eddy current inspection for cracking of the forward fastener row of any external doubler repair common to the rear spar lower chord between STA 83.50 and STA 249.10. (i) Service Information Exceptions (1) Where SASB 737-55-1059 R1 specifies a compliance time ``after the Revision 1 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, corrosion, hole elongation, or loose or missing fastener is found during any inspection required by this AD, and SASB 737-55-1059 R1 specifies to contact Boeing for repair instructions: Before further flight, repair the cracking, corrosion, hole elongation, loose or missing fasteners using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (3) Where SASB 737-55-1059 R1 specifies that doublers installed with solid rivets do not need to be inspected for loose or missing fasteners, this AD does not require doublers installed with solid rivets or Hi-lok fasteners to be inspected for loose or missing fasteners. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles 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, 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, 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 For more information about this AD, contact George Garrido, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627- 5232; fax: 562-627-5210; email: [email protected]. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Special Attention Service Bulletin 737-55-1059, Revision 1, dated April 6, 2016. (ii) Reserved. (3) For Boeing service information identified in this AD, contact Boeing [[Page 15287]] 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. (4) You may view this 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on March 16, 2017. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-05768 Filed 3-27-17; 8:45 am] BILLING CODE 4910-13-P
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DEPARTMENT OF TRANSPORTATION Docket Management Facility, U.S. the inspection area specified in SASB
Department of Transportation, Docket 737–55–1059 R1.
Federal Aviation Administration Operations, M–30, West Building We agree with ANA’s request.
Ground Floor, Room W12–140, 1200 Specifying the location of the applicable
14 CFR Part 39 New Jersey Avenue SE., Washington, repairs may reduce potential confusion.
DC 20590. Therefore, we have revised paragraphs
[Docket No. FAA–2016–9068; Directorate
Identifier 2016–NM–067–AD; Amendment FOR FURTHER INFORMATION CONTACT: (h)(1), (h)(2), and (h)(3) of this AD to
39–18838; AD 2017–06–14] George Garrido, Aerospace Engineer, specify the location of the applicable
Airframe Branch, ANM–120L, FAA, Los repairs.
RIN 2120–AA64
Angeles Aircraft Certification Office Request To Clarify Fastener
Airworthiness Directives; The Boeing (ACO), 3960 Paramount Boulevard, Requirements
Company Airplanes Lakewood, CA 90712–4137; phone:
562–627–5232; fax: 562–627–5210; ANA requested that we clarify the
AGENCY: Federal Aviation email: george.garrido@faa.gov. fastener requirements. ANA stated that
Administration (FAA), DOT. figure 3 in Boeing Special Attention
SUPPLEMENTARY INFORMATION:
Service Bulletin 737–55–1059, dated
ACTION: Final rule.
Discussion September 10, 1998, specifies to use
SUMMARY: We are adopting a new We issued a notice of proposed blind rivets and Hi-lok fasteners;
airworthiness directive (AD) for certain rulemaking (NPRM) to amend 14 CFR however, compliance table 2, note (b),
The Boeing Company Model 737–300, part 39 by adding an AD that would in SASB 737–55–1059 R1, states that
–400, and –500 series airplanes. This apply to certain The Boeing Company doublers installed with solid rivets do
AD was prompted by reports of cracks Model 737–300, –400, and –500 series not need to be inspected for any loose
in the horizontal stabilizer lower skins. airplanes. The NPRM published in the or missing fasteners. ANA explained
This AD requires inspections for Federal Register on September 8, 2016 that Boeing told ANA that Hi-lok
cracking of the horizontal stabilizer (81 FR 62022) (‘‘the NPRM’’). The fasteners do not require inspection for
lower skin, and corrective actions if NPRM was prompted by reports of any loose or missing fasteners.
necessary; and also provides actions cracks in the horizontal stabilizer lower We agree to clarify the fastener
that would terminate certain repetitive skins. The NPRM proposed to require requirements. We infer that ANA is
inspections. We are issuing this AD to inspections for cracking of the requesting that we update paragraph (h)
address the unsafe condition on these horizontal stabilizer lower skin, of this AD to specify that Hi-lok
products. including repetitive inspections, as fasteners do not require inspection. We
applicable, and corrective actions if have determined that Hi-lok fasteners
DATES: This AD is effective May 2, 2017. do not require inspection. Therefore, we
The Director of the Federal Register necessary; and also proposed actions
that would terminate certain repetitive have added paragraph (i)(3) to this AD
approved the incorporation by reference to specify that where SASB 737–55–
of a certain publication listed in this AD inspections. We are issuing this AD to
detect and correct cracks in horizontal 1059 R1 specifies that doublers installed
as of May 2, 2017. with solid rivets do not need to be
stabilizer lower skins resulting in
ADDRESSES: For service information inspected for loose or missing fasteners,
reduced local stiffness of the horizontal
identified in this final rule, contact this AD does not require doublers
stabilizer, which can cause heavy
Boeing Commercial Airplanes, installed with solid rivets or Hi-lok
vibration leading to loss of structural
Attention: Contractual & Data Services fasteners to be inspected for loose or
integrity of the horizontal stabilizer.
(C&DS), 2600 Westminster Blvd., MC missing fasteners. We have also revised
110–SK57, Seal Beach, CA 90740–5600; Comments paragraph (h)(1) of this AD to reference
telephone 562–797–1717; Internet We gave the public the opportunity to this exception.
https://www.myboeingfleet.com. You participate in developing this AD. The
may view this referenced service Request To Revise Configuration
following presents the comments Description
information at the FAA, Transport received on the NPRM and the FAA’s
Airplane Directorate, 1601 Lind Avenue response to each comment. ANA requested that we revise
SW., Renton, WA. For information on paragraph (h) of the proposed AD to
the availability of this material at the Support for the NPRM refer to the horizontal stabilizer
FAA, call 425–227–1221. It is also Boeing expressed support for the configuration with the applicable repair
available on the Internet at http:// NPRM. installed side only. ANA asserted that
www.regulations.gov by searching for the wording of paragraph (h) of the
Request To Revise Repair Instructions proposed AD could be interpreted to
and locating Docket No. FAA–2016–
9068. All Nippon Airways (ANA) requested require inspection of both the repaired
that we revise paragraphs (h)(1) and and unrepaired sides of the horizontal
Examining the AD Docket (h)(3) of the proposed AD to state stabilizer.
You may examine the AD docket on ‘‘repair common to the rear spar lower We agree with ANA’s request. The
the Internet at http:// chord between station (STA) 83.50 and wording in the proposed AD is not clear
www.regulations.gov by searching for STA 249.10,’’ instead of ‘‘repair.’’ ANA regarding what is required if an airplane
and locating Docket No. FAA–2016– stated that there might be a repair has left and right stabilizers that are
9068; or in person at the Docket installed on the lower skin of the different configurations. For example,
mstockstill on DSK3G9T082PROD with RULES
Management Facility between 9 a.m. horizontal stabilizer that is not the left-side stabilizer may have a repair
and 5 p.m., Monday through Friday, addressed in Boeing Special Attention installed common to the rear spar lower
except Federal holidays. The AD docket Service Bulletin 737–55–1059, Revision chord (configuration 2), whereas the
contains this AD, the regulatory 1, dated April 6, 2016 (‘‘SASB 737–55– right side may not have a repair
evaluation, any comments received, and 1059 R1’’). ANA explained that some (configuration 1). We have revised the
other information. The address for the structural repair manual repairs and affected airplanes in paragraph (g) of
Docket Office (phone: 800–647–5527) is external doublers are not applicable to this AD from ‘‘Group 1, Configuration 1,
VerDate Sep<11>2014 16:44 Mar 27, 2017 Jkt 241001 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 E:\FR\FM\28MRR1.SGM 28MRR1](https://thefederalregister.org/doc/82_FR_15342/page/1.svg)
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Adoption of the Amendment in SASB 737–55–1059 R1: Except as of this service bulletin,’’ this AD requires
specified in paragraph (i)(1) of this AD, at the compliance within the specified compliance
Accordingly, under the authority applicable time specified in paragraph 1.E., time after the effective date of this AD.
delegated to me by the Administrator, ‘‘Compliance,’’ of SASB 737–55–1059 R1, do (2) If any cracking, corrosion, hole
the FAA amends 14 CFR part 39 as a detailed inspection for cracking of the elongation, or loose or missing fastener is
follows: horizontal stabilizer lower skin; and do all found during any inspection required by this
applicable related investigative and AD, and SASB 737–55–1059 R1 specifies to
PART 39—AIRWORTHINESS corrective actions; in accordance with the contact Boeing for repair instructions: Before
DIRECTIVES Accomplishment Instructions of SASB 737– further flight, repair the cracking, corrosion,
55–1059 R1, except as specified in paragraph hole elongation, loose or missing fasteners
■ 1. The authority citation for part 39 (i)(2) of this AD. Do all applicable related using a method approved in accordance with
continues to read as follows: investigative and corrective actions before the procedures specified in paragraph (j) of
further flight. Repeat the inspection of the this AD.
Authority: 49 U.S.C. 106(g), 40113, 44701. horizontal stabilizer lower skin, if applicable, (3) Where SASB 737–55–1059 R1 specifies
thereafter at the applicable intervals specified that doublers installed with solid rivets do
§ 39.13 [Amended]
in paragraph 1.E., ‘‘Compliance,’’ of SASB not need to be inspected for loose or missing
■ 2. The FAA amends § 39.13 by adding 737–55–1059 R1. Options specified in SASB fasteners, this AD does not require doublers
the following new airworthiness 737–55–1059 R1 for accomplishing the installed with solid rivets or Hi-lok fasteners
directive (AD): inspections are acceptable for the to be inspected for loose or missing fasteners.
corresponding requirements of this paragraph
2017–06–14 The Boeing Company: provided that the inspections are done at the (j) Alternative Methods of Compliance
Amendment 39–18838; Docket No. applicable times in paragraph 1.E., (AMOCs)
FAA–2016–9068; Directorate Identifier ‘‘Compliance,’’ of the SASB 737–55–1059 R1. (1) The Manager, Los Angeles Aircraft
2016–NM–067–AD. Certification Office (ACO), FAA, has the
(h) Inspections, Related Investigative authority to approve AMOCs for this AD, if
(a) Effective Date Actions, and Corrective Actions for requested using the procedures found in 14
This AD is effective May 2, 2017. Configuration 2 Horizontal Stabilizers on CFR 39.19. In accordance with 14 CFR 39.19,
Group 1 Airplanes send your request to your principal inspector
(b) Affected ADs
For any Configuration 2 horizontal or local Flight Standards District Office, as
None.
stabilizer on Group 1 airplanes, as identified appropriate. If sending information directly
(c) Applicability in SASB 737–55–1059 R1: Except as to the manager of the ACO, send it to the
(1) This AD applies to The Boeing specified in paragraph (i)(1) of this AD, at the attention of the person identified in
Company Model 737–300, –400, and –500 applicable time specified in paragraph 1.E., paragraph (k) of this AD. Information may be
series airplanes, certificated in any category, ‘‘Compliance,’’ of SASB 737–55–1059 R1, do emailed to: 9-ANM-LAACO-AMOC-
as identified in Boeing Special Attention the actions specified in paragraphs (h)(1), Requests@faa.gov.
Service Bulletin 737–55–1059, Revision 1, (h)(2), and (h)(3) of this AD; and do all (2) Before using any approved AMOC,
dated April 6, 2016 (‘‘SASB 737–55–1059 applicable related investigative and notify your appropriate principal inspector,
R1’’). corrective actions; in accordance with the or lacking a principal inspector, the manager
(2) Installation of Supplemental Type Accomplishment Instructions of SASB 737– of the local flight standards district office/
Certificate (STC) ST01219SE (http:// 55–1059 R1, except as specified in paragraph certificate holding district office.
rgl.faa.gov/Regulatory_and_Guidance_ (i)(2) of this AD. Do all applicable related (3) An AMOC that provides an acceptable
Library/rgstc.nsf/0/ investigative and corrective actions before level of safety may be used for any repair,
ebd1cec7b301293e86257cb30045557a/$FILE/ further flight. Repeat the inspections modification, or alteration required by this
ST01219SE.pdf) does not affect the ability to specified in paragraphs (h)(1), (h)(2), and AD if it is approved by the Boeing
accomplish the actions required by this AD. (h)(3) of this AD, if applicable, thereafter at Commercial Airplanes Organization
Therefore, for airplanes on which STC the applicable intervals specified in Designation Authorization (ODA) that has
ST01219SE is installed, a ‘‘change in paragraph 1.E., ‘‘Compliance,’’ of SASB 737– been authorized by the Manager, Los Angeles
product’’ alternative method of compliance 55–1059 R1. Options specified in SASB 737– ACO, to make those findings. To be
(AMOC) approval request is not necessary to 55–1059 R1, for accomplishing the approved, the repair method, modification
comply with the requirements of 14 CFR inspections are acceptable for the deviation, or alteration deviation must meet
39.17. corresponding requirements of this paragraph the certification basis of the airplane, and the
provided that the inspections are done at the approval must specifically refer to this AD.
(d) Subject applicable times in paragraph 1.E.,
‘‘Compliance,’’ of SASB 737–55–1059 R1. (k) Related Information
Air Transport Association (ATA) of
America Code 55; Horizontal stabilizer. (1) Do a high frequency eddy current For more information about this AD,
inspection for cracking of the skin around contact George Garrido, Aerospace Engineer,
(e) Unsafe Condition any repair common to the rear spar lower Airframe Branch, ANM–120L, FAA, Los
This AD was prompted by reports of cracks chord between station (STA) 83.50 and STA Angeles ACO, 3960 Paramount Boulevard,
in horizontal stabilizer lower skins. We are 249.10 which was done as specified in the Lakewood, CA 90712–4137; phone: 562–627–
issuing this AD to detect and correct cracks structural repair manual or any external 5232; fax: 562–627–5210; email:
in horizontal stabilizer lower skins, resulting doubler repair, and a detailed inspection for george.garrido@faa.gov.
in reduced local stiffness of the stabilizer, any loose or any missing fastener of repaired
(l) Material Incorporated by Reference
which can cause heavy vibration leading to doublers, except as specified in paragraph
loss of structural integrity of the horizontal (i)(3) of this AD. (1) The Director of the Federal Register
stabilizer. (2) Do a detailed inspection for cracking of approved the incorporation by reference
the inspar lower skin between STA 83.50 and (IBR) of the service information listed in this
(f) Compliance STA 249.10, except in areas repaired paragraph under 5 U.S.C. 552(a) and 1 CFR
Comply with this AD within the common to the rear spar lower chord. part 51.
compliance times specified, unless already (3) Do a low frequency eddy current (2) You must use this service information
mstockstill on DSK3G9T082PROD with RULES
done. inspection for cracking of the forward as applicable to do the actions required by
fastener row of any external doubler repair this AD, unless the AD specifies otherwise.
(g) Inspections, Related Investigative (i) Boeing Special Attention Service
common to the rear spar lower chord
Actions, and Corrective Actions for between STA 83.50 and STA 249.10. Bulletin 737–55–1059, Revision 1, dated
Configuration 1 Horizontal Stabilizers on April 6, 2016.
Group 1 Airplanes (i) Service Information Exceptions (ii) Reserved.
For any Configuration 1 horizontal (1) Where SASB 737–55–1059 R1 specifies (3) For Boeing service information
stabilizer on Group 1 airplanes, as identified a compliance time ‘‘after the Revision 1 date identified in this AD, contact Boeing
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![Federal Register / Vol. 82, No. 58 / Tuesday, March 28, 2017 / Rules and Regulations 15287
Commercial Airplanes, Attention: 6215; fax 316–517–5802; email bulkhead. Loss of bond integrity could
Contractual & Data Services (C&DS), 2600 citationpubs@txtav.com; Internet result in a structural failure that could
Westminster Blvd., MC 110–SK57, Seal https://support.cessna.com/custsupt/ lead to separation of the cruciform tail
Beach, CA 90740–5600; telephone 562–797– and loss of control of the airplane.
csupport/newlogin.jsp. You may review
1717; Internet https://
www.myboeingfleet.com. this referenced service information at Comments
(4) You may view this service information the FAA, Transport Airplane
at the FAA, Transport Airplane Directorate, Directorate, 1601 Lind Avenue SW., We gave the public the opportunity to
1601 Lind Avenue SW., Renton, WA. For Renton, WA. For information on the participate in developing this AD. The
information on the availability of this availability of this material at the FAA, following presents the comments
material at the FAA, call 425–227–1221. call 425–227–1221. It is also available received on the NPRM and the FAA’s
(5) You may view this service information on the Internet at http:// response to each comment.
that is incorporated by reference at the
www.regulations.gov by searching for Request To Limit Findings to
National Archives and Records
Administration (NARA). For information on and locating Docket No. FAA–2016– ‘‘Disbonding’’
the availability of this material at NARA, call 3705.
NetJets Aviation, Inc. (NetJets)
202–741–6030, or go to: http:// Examining the AD Docket requested that we revise paragraph (h)
www.archives.gov/federal-register/cfr/ibr-
locations.html. You may examine the AD docket on of the proposed AD to remove ‘‘cracked
the Internet at http:// paint’’ as a possible finding from the
Issued in Renton, Washington, on March inspection. NetJets acknowledged that
16, 2017. www.regulations.gov by searching for
and locating Docket No. FAA–2016– cracked paint, while not a safety
Dionne Palermo, concern on its own, should be
Acting Manager, Transport Airplane
3705; or in person at the Docket
Management Facility between 9 a.m. investigated to ensure that it is not
Directorate, Aircraft Certification Service. evidence of disbonding. NetJets
and 5 p.m., Monday through Friday,
[FR Doc. 2017–05768 Filed 3–27–17; 8:45 am]
except Federal holidays. The AD docket indicated that the requirement for a
BILLING CODE 4910–13–P
contains this AD, the regulatory disbond to be repaired per an alternative
evaluation, any comments received, and method of compliance (AMOC) is
other information. The address for the sufficient to ensure that the safety
DEPARTMENT OF TRANSPORTATION concern is addressed appropriately.
Docket Office (phone: 800–647–5527) is
We agree with the commenter that
Federal Aviation Administration Docket Management Facility, U.S.
cracked paint may not be a safety
Department of Transportation, Docket
concern on its own; however it is
14 CFR Part 39 Operations, M–30, West Building
evidence that a disbond of the structure
Ground Floor, Room W12–140, 1200
[Docket No. FAA–2016–3705; Directorate may have occurred and should be
New Jersey Avenue SE., Washington,
Identifier 2015–NM–168–AD; Amendment investigated further to ensure there is no
DC 20590.
39–18837; AD 2017–06–13] evidence of disbonding. Thus, if cracked
FOR FURTHER INFORMATION CONTACT: paint is found, operators must contact
RIN 2120–AA64 Phuoc Le, Aerospace Engineer, Airframe the FAA for procedures to determine
Branch, ACE–118W, Wichita Aircraft whether the cracked paint was an
Airworthiness Directives; Textron
Certification Office (ACO), FAA, 1801 indication of disbonding. We have
Aviation Inc. (Type Certificate
Airport Road, Room 100, Dwight D. revised paragraph (h) of this AD to
Previously Held by Cessna Aircraft
Eisenhower Airport, Wichita, KS 67209; clarify that operators must obtain
Company) Airplanes
phone: 316–946–4195; fax: 316–946– instructions from the FAA and comply
AGENCY: Federal Aviation 4107; email: phuoc.le@faa.gov. with those instructions.
Administration (FAA), DOT. SUPPLEMENTARY INFORMATION:
ACTION: Final rule. Request To Have Cessna Engineering
Discussion Drawing Be Made Available
SUMMARY: We are adopting a new We issued a notice of proposed NetJets indicated that paragraph (n)(2)
airworthiness directive (AD) for certain rulemaking (NPRM) to amend 14 CFR of the proposed AD states that the
Textron Aviation Inc. (Textron) Model part 39 by adding an AD that would required service information is available
680 airplanes. This AD was prompted apply to certain Textron Aviation Inc. from Textron. However, Netjets stated
by Textron’s report of a manufacturing Model 680 airplanes. The NPRM that Textron does not provide owners/
defect that affects the durability of the published in the Federal Register on operators with access to Cessna
aft canted bulkhead metallic structure. February 26, 2016 (81 FR 9790) (‘‘the Engineering Drawing 6991115
This AD requires repetitive inspections NPRM’’). The NPRM was prompted by (‘‘Drawing 6991115’’), which is required
of the aft canted bulkhead; repair if Textron’s report of a manufacturing for compliance with paragraph (i) of the
necessary; and a modification, which defect that affects the durability of the proposed AD. NetJets added that the
would terminate the repetitive aft canted bulkhead metallic structure. required service information is not
inspections. We are issuing this AD to The manufacturing defect directly available at the Federal Register and is
address the unsafe condition on these affects the bond integrity of the vertical not available to owners/operators
products. and horizontal stiffeners on the aft through the source identified in the
DATES: This AD is effective May 2, 2017. canted bulkhead metallic structure. The proposed AD. NetJets indicated that
The Director of the Federal Register NPRM proposed to require repetitive Cessna Service Bulletin SB680–53–08,
mstockstill on DSK3G9T082PROD with RULES
approved the incorporation by reference inspections of the aft canted bulkhead dated September 28, 2015, states that
of certain publications listed in this AD and repair if necessary. The NPRM also only Textron-owned service centers can
as of May 2, 2017. proposed to require a modification complete the modification and have
ADDRESSES: For service information which would terminate the repetitive access to Drawing 6991115. NetJets
identified in this final rule, contact inspections. We are issuing this AD to stated that access to Drawing 6991115
Textron Aviation Inc., P.O. Box 7706, prevent disbonding of the horizontal should be made available to owners/
Wichita, KS 67277; telephone 316–517– and vertical stiffeners on the aft canted operators, and the proposed AD should
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Document Created: 2017-03-28 00:32:35
Document Modified: 2017-03-28 00:32:35
| 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 | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective May 2, 2017. | |
| Contact | George Garrido, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5232; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 82 FR 15284 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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