81 FR 56540 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 162 (August 22, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 162 (August 22, 2016)
| Page Range | 56540-56542 | |
| FR Document | 2016-19936 |
[Federal Register Volume 81, Number 162 (Monday, August 22, 2016)] [Proposed Rules] [Pages 56540-56542] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-19936] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-8845; Directorate Identifier 2016-NM-094-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 DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD- 83), and DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes. This proposed AD was prompted by a report of fatigue cracking in a rear spar lower cap of the horizontal stabilizer. This proposed AD would require repetitive inspections for cracking of the rear spar lower caps of the horizontal stabilizer, post-modification and post-repair inspections, and corrective actions if necessary. This proposed AD also provides an optional terminating fatigue life enhancement modification. We are proposing this AD to detect and correct fatigue cracking in the rear spar lower caps of the horizontal stabilizer, which, paired with cracking in adjacent areas, could adversely affect the structural integrity of the airplane. DATES: We must receive comments on this proposed AD by October 6, 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 NPRM, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; telephone 206-544-5000, extension 2; fax 206-766-5683; 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- 8845. 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- 8845; 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: Haytham Alaidy, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5224; 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-2016-8845; Directorate Identifier 2016-NM-094-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. [[Page 56541]] Discussion We have received a report of a 0.513-inch crack in a rear spar lower cap of the horizontal stabilizer. The Model MD-88 airplane had accumulated 61,741 total flight hours and 45,985 total landing cycles. Lab analysis on the area adjacent to the crack shows that the crack was caused by fatigue. Such fatigue cracking, paired with cracking in adjacent areas, could adversely affect the structural integrity of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin MD80-55A072, dated April 8, 2016. The service information describes procedures for doing inspections for cracking of the rear spar lower caps of the horizontal stabilizer, post-modification and post-repair inspections, and repairs. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA's Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of these same type designs. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ``Differences Between this Proposed AD and the Service Information.'' For information on the procedures and compliance times, see this service information at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-8845. The phrase ``corrective actions'' is used in this proposed AD. Corrective actions correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin MD80-55A072, dated April 8, 2016, specifies to contact the manufacturer for certain instructions, but this proposed AD would require accomplishment of repair methods, modification deviations, and alteration deviations in one of the following ways: In accordance with a method that we approve; or Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Costs of Compliance We estimate that this proposed AD affects 395 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspection..................... 3 work-hours x $85 per $0 $255 per $100,725 per hour = $255 per inspection cycle. inspection inspection cycle. cycle. ---------------------------------------------------------------------------------------------------------------- Estimated Costs for Optional Actions ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Modification......................... 59 work-hours x $85 per hour $1,267 $6,282 per stabilizer. = $ 5,015 per stabilizer. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary replacement 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 this replacement: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Replacement.......................... 368 work-hours x $85 per hour $31,408 $62,688 per stabilizer. = $31,280 per stabilizer. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition actions that require repair using a method specified in paragraph (k) of 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. 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, [[Page 56542]] (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-2016-8845; Directorate Identifier 2016-NM-094-AD. (a) Comments Due Date We must receive comments by October 6, 2016. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes; certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 55, Stabilizers. (e) Unsafe Condition This AD was prompted by a report of fatigue cracking in a Model MD-88 rear spar lower cap of the horizontal stabilizer. We are issuing this AD to detect and correct fatigue cracking in the rear spar lower caps of the horizontal stabilizer, which, paired with cracking in adjacent areas, could adversely affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections and Corrective Actions Except as specified in paragraph (i)(1) of this AD, at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin MD80-55A072, dated April 08, 2016: Do an open hole high frequency eddy current inspection (HFEC) or surface HFEC inspection for cracking of the rear spar lower caps of the horizontal stabilizer, and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80-55A072, dated April 8, 2016, except as specified in paragraph (i)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection thereafter at the applicable interval specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin MD80-55A072, dated April 8, 2016, until accomplishment of the actions provided by paragraph (h) of this AD. (h) Optional Terminating Action Accomplishment of the fatigue life enhancement modification in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80-55A072, dated April 8, 2016, terminates the repetitive inspections required by paragraph (g) of this AD. (i) Service Information Exceptions (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin MD80-55A072, dated April 8, 2016, 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 MD80-55A072, dated April 8, 2016, specifies to contact Boeing for appropriate action: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (j) Post-Modification and Post-Repair Actions For airplanes on which any modification or repair specified in (g) or (h) of this AD has been done: At the applicable time and intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin MD80-55A072, dated April 8, 2016, do all applicable post-modification and post-repair inspections and all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80-55A072, dated April 8, 2016; except as specified in paragraph (i)(2) of this AD. All applicable corrective actions must be done before further flight. (k) 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 (l)(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, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) Except as required by paragraph (i)(2) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (k)(4)(i) and (k)(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. If a step or sub-step is labeled ``RC Exempt,'' then the RC requirement is removed from that step or sub-step. 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. (l) Related Information (1) For more information about this AD, contact Haytham Alaidy, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5224; fax: 562-627-5210; email: [email protected]. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; telephone 206-544-5000, extension 2; fax 206-766-5683; 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 August 11, 2016. Paul R. Bernado, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-19936 Filed 8-19-16; 8:45 am] BILLING CODE 4910-13-P
![56540 Federal Register / Vol. 81, No. 162 / Monday, August 22, 2016 / Proposed Rules
(k) Alternative Methods of Compliance Issued in Renton, WA, on August 11, 2016. Airplanes, Attention: Data & Services
(AMOCs) Paul R. Bernado, Management, 3855 Lakewood
(1) The Manager, Seattle Aircraft Acting Manager, Transport Airplane Boulevard, MC D800–0019, Long Beach,
Certification Office (ACO), FAA, has the Directorate, Aircraft Certification Service. CA 90846–0001; telephone 206–544–
authority to approve AMOCs for this AD, if [FR Doc. 2016–19935 Filed 8–19–16; 8:45 am] 5000, extension 2; fax 206–766–5683;
requested using the procedures found in 14 BILLING CODE 4910–13–P Internet https://
CFR 39.19. In accordance with 14 CFR 39.19, www.myboeingfleet.com. You may view
send your request to your principal inspector this referenced service information at
or local Flight Standards District Office, as DEPARTMENT OF TRANSPORTATION the FAA, Transport Airplane
appropriate. If sending information directly Directorate, 1601 Lind Avenue SW.,
to the manager of the ACO, send it to the Federal Aviation Administration Renton, WA. For information on the
attention of the person identified in availability of this material at the FAA,
paragraph (l)(1) of this AD. Information may 14 CFR Part 39 call 425–227–1221. It is also available
be emailed to: 9-ANM-Seattle-ACO-AMOC- on the internet at http://
[Docket No. FAA–2016–8845; Directorate
Requests@faa.gov. www.regulations.gov by searching for
Identifier 2016–NM–094–AD]
(2) Before using any approved AMOC,
and locating Docket No. FAA–2016–
notify your appropriate principal inspector, RIN 2120–AA64
8845.
or lacking a principal inspector, the manager
of the local flight standards district office/ Airworthiness Directives; The Boeing Examining the AD Docket
certificate holding district office. Company Airplanes
You may examine the AD docket on
(3) An AMOC that provides an acceptable AGENCY: Federal Aviation
level of safety may be used for any repair,
the Internet at http://
Administration (FAA), DOT. www.regulations.gov by searching for
modification, or alteration required by this
ACTION: Notice of proposed rulemaking and locating Docket No. FAA–2016–
AD if it is approved by the Boeing
Commercial Airplanes Organization (NPRM). 8845; or in person at the Docket
Designation Authorization (ODA) that has Management Facility between 9 a.m.
SUMMARY: We propose to adopt a new and 5 p.m., Monday through Friday,
been authorized by the Manager, Seattle airworthiness directive (AD) for all The
ACO, to make those findings. To be except Federal holidays. The AD docket
Boeing Company Model DC–9–81 (MD– contains this proposed AD, the
approved, the repair method, modification
81), DC–9–82 (MD–82), DC–9–83 (MD– regulatory evaluation, any comments
deviation, or alteration deviation must meet
83), and DC–9–87 (MD–87) airplanes;
the certification basis of the airplane and the received, and other information. The
and Model MD–88 airplanes. This
approval must specifically refer to this AD. street address for the Docket Office
proposed AD was prompted by a report
(i) For service information that contains (phone: 800–647–5527) is in the
of fatigue cracking in a rear spar lower
steps that are labeled as Required for ADDRESSES section. Comments will be
Compliance (RC), the provisions of cap of the horizontal stabilizer. This
available in the AD docket shortly after
paragraphs (k)(3)(i) and (k)(3)(ii) of this AD proposed AD would require repetitive
receipt.
apply. The steps labeled as RC, including inspections for cracking of the rear spar
lower caps of the horizontal stabilizer, FOR FURTHER INFORMATION CONTACT:
substeps under an RC step and any figures
post-modification and post-repair Haytham Alaidy, Aerospace Engineer,
identified in an RC step, must be done to
inspections, and corrective actions if Airframe Branch, ANM–120L, FAA, Los
comply with the AD. An AMOC is required
necessary. This proposed AD also Angeles Aircraft Certification Office
for any deviations to RC steps, including
substeps and identified figures. provides an optional terminating fatigue (ACO), 3960 Paramount Boulevard,
(ii) Steps not labeled as RC may be life enhancement modification. We are Lakewood, CA 90712–4137; phone:
deviated from using accepted methods in proposing this AD to detect and correct 562–627–5224; fax: 562–627–5210;
accordance with the operator’s maintenance fatigue cracking in the rear spar lower email: haytham.alaidy@faa.gov.
or inspection program without obtaining caps of the horizontal stabilizer, which, SUPPLEMENTARY INFORMATION:
approval of an AMOC, provided the RC steps, paired with cracking in adjacent areas, Comments Invited
including substeps and identified figures, can could adversely affect the structural
still be done as specified, and the airplane integrity of the airplane. We invite you to send any written
can be put back in an airworthy condition. DATES: We must receive comments on relevant data, views, or arguments about
this proposed AD by October 6, 2016. this proposal. Send your comments to
(l) Related Information
ADDRESSES: You may send comments,
an address listed under the ADDRESSES
(1) For more information about this AD, section. Include ‘‘Docket No. FAA–
contact Alan Pohl, Aerospace Engineer, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following 2016–8845; Directorate Identifier 2016–
Airframe Branch, ANM–120S, FAA, Seattle NM–094–AD’’ at the beginning of your
Aircraft Certification Office, 1601 Lind methods:
• Federal eRulemaking Portal: Go to comments. We specifically invite
Avenue SW., Renton, WA 98057–3356;
http://www.regulations.gov. Follow the comments on the overall regulatory,
phone: 425–917–6450; fax: 425–917–6590;
instructions for submitting comments. economic, environmental, and energy
email: alan.pohl@faa.gov.
(2) For service information identified in • Fax: 202–493–2251. aspects of this proposed AD. We will
this AD, contact Boeing Commercial • Mail: U.S. Department of consider all comments received by the
Airplanes, Attention: Data & Services Transportation, Docket Operations, M– closing date and may amend this
Management, P.O. Box 3707, MC 2H–65, 30, West Building Ground Floor, Room proposed AD because of those
comments.
Lhorne on DSK30JT082PROD with PROPOSALS
Seattle, WA 98124–2207; telephone 206– W12–140, 1200 New Jersey Avenue SE.,
544–5000, extension 1; fax 206–766–5680; Washington, DC 20590. We will post all comments we
Internet https://www.myboeingfleet.com. You • Hand Delivery: Deliver to Mail receive, without change, to http://
may view this referenced service information address above between 9 a.m. and 5 www.regulations.gov, including any
at the FAA, Transport Airplane Directorate, p.m., Monday through Friday, except personal information you provide. We
1601 Lind Avenue SW., Renton, WA. For Federal holidays. will also post a report summarizing each
information on the availability of this For service information identified in substantive verbal contact we receive
material at the FAA, call 425–227–1221. this NPRM, contact Boeing Commercial about this proposed AD.
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![56542 Federal Register / Vol. 81, No. 162 / Monday, August 22, 2016 / Proposed Rules
(2) Is not a ‘‘significant rule’’ under (g) Repetitive Inspections and Corrective appropriate. If sending information directly
the DOT Regulatory Policies and Actions to the manager of the ACO, send it to the
Procedures (44 FR 11034, February 26, Except as specified in paragraph (i)(1) of attention of the person identified in
this AD, at the applicable time specified in paragraph (l)(1) of this AD. Information may
1979), be emailed to: 9-ANM-LAACO-AMOC-
paragraph 1.E., ‘‘Compliance,’’ of Boeing
(3) Will not affect intrastate aviation Alert Service Bulletin MD80–55A072, dated Requests@faa.gov.
in Alaska, and April 08, 2016: Do an open hole high (2) Before using any approved AMOC,
frequency eddy current inspection (HFEC) or notify your appropriate principal inspector,
(4) Will not have a significant or lacking a principal inspector, the manager
economic impact, positive or negative, surface HFEC inspection for cracking of the
of the local flight standards district office/
rear spar lower caps of the horizontal
on a substantial number of small entities certificate holding district office.
stabilizer, and do all applicable corrective
under the criteria of the Regulatory actions; in accordance with the
(3) An AMOC that provides an acceptable
Flexibility Act. level of safety may be used for any repair,
Accomplishment Instructions of Boeing Alert
modification, or alteration required by this
List of Subjects in 14 CFR Part 39 Service Bulletin MD80–55A072, dated April
AD if it is approved by the Boeing
8, 2016, except as specified in paragraph
Commercial Airplanes Organization
Air transportation, Aircraft, Aviation (i)(2) of this AD. Do all applicable corrective Designation Authorization (ODA) that has
safety, Incorporation by reference, actions before further flight. Repeat the been authorized by the Manager, Los Angeles
inspection thereafter at the applicable ACO, to make those findings. To be
Safety. interval specified in paragraph 1.E., approved, the repair method, modification
The Proposed Amendment ‘‘Compliance,’’ of Boeing Alert Service deviation, or alteration deviation must meet
Bulletin MD80–55A072, dated April 8, 2016, the certification basis of the airplane, and the
Accordingly, under the authority until accomplishment of the actions provided approval must specifically refer to this AD.
delegated to me by the Administrator, by paragraph (h) of this AD. (4) Except as required by paragraph (i)(2)
the FAA proposes to amend 14 CFR part (h) Optional Terminating Action of this AD: For service information that
39 as follows: contains steps that are labeled as Required
Accomplishment of the fatigue life for Compliance (RC), the provisions of
enhancement modification in accordance paragraphs (k)(4)(i) and (k)(4)(ii) of this AD
PART 39—AIRWORTHINESS with the Accomplishment Instructions of apply.
DIRECTIVES Boeing Alert Service Bulletin MD80–55A072, (i) The steps labeled as RC, including
dated April 8, 2016, terminates the repetitive substeps under an RC step and any figures
■ 1. The authority citation for part 39 inspections required by paragraph (g) of this identified in an RC step, must be done to
continues to read as follows: AD. comply with the AD. If a step or sub-step is
(i) Service Information Exceptions labeled ‘‘RC Exempt,’’ then the RC
Authority: 49 U.S.C. 106(g), 40113, 44701. requirement is removed from that step or
(1) Where paragraph 1.E., ‘‘Compliance,’’ of sub-step. An AMOC is required for any
§ 39.13 [Amended] Boeing Alert Service Bulletin MD80–55A072, deviations to RC steps, including substeps
■ 2. The FAA amends § 39.13 by adding dated April 8, 2016, specifies a compliance and identified figures.
the following new airworthiness time ‘‘after the original issue date of this (ii) Steps not labeled as RC may be
service bulletin,’’ this AD requires deviated from using accepted methods in
directive (AD): compliance within the specified compliance accordance with the operator’s maintenance
The Boeing Company: Docket No. FAA– time after the effective date of this AD. or inspection program without obtaining
2016–8845; Directorate Identifier 2016– (2) If any cracking is found during any approval of an AMOC, provided the RC steps,
NM–094–AD. inspection required by this AD, and Boeing including substeps and identified figures, can
(a) Comments Due Date Alert Service Bulletin MD80–55A072, dated still be done as specified, and the airplane
April 8, 2016, specifies to contact Boeing for can be put back in an airworthy condition.
We must receive comments by October 6, appropriate action: Before further flight,
2016. (l) Related Information
repair the cracking using a method approved
in accordance with the procedures specified (1) For more information about this AD,
(b) Affected ADs contact Haytham Alaidy, Aerospace
in paragraph (k) of this AD.
None. Engineer, Airframe Branch, ANM–120L,
(j) Post-Modification and Post-Repair FAA, Los Angeles Aircraft Certification
(c) Applicability Actions Office (ACO), 3960 Paramount Boulevard,
This AD applies to all The Boeing For airplanes on which any modification or Lakewood, CA 90712–4137; phone: 562–627–
Company Model DC–9–81 (MD–81), DC–9– repair specified in (g) or (h) of this AD has 5224; fax: 562–627–5210; email:
82 (MD–82), DC–9–83 (MD–83), and DC–9– been done: At the applicable time and haytham.alaidy@faa.gov.
87 (MD–87) airplanes; and Model MD–88 intervals specified in paragraph 1.E., (2) For service information identified in
airplanes; certificated in any category. ‘‘Compliance,’’ of Boeing Alert Service this AD, contact Boeing Commercial
Bulletin MD80–55A072, dated April 8, 2016, Airplanes, Attention: Data & Services
(d) Subject Management, 3855 Lakewood Boulevard, MC
do all applicable post-modification and post-
Air Transport Association (ATA) of repair inspections and all applicable D800–0019, Long Beach, CA 90846–0001;
America Code 55, Stabilizers. corrective actions; in accordance with the telephone 206–544–5000, extension 2; fax
Accomplishment Instructions of Boeing Alert 206–766–5683; Internet https://
(e) Unsafe Condition www.myboeingfleet.com. You may view this
Service Bulletin MD80–55A072, dated April
This AD was prompted by a report of 8, 2016; except as specified in paragraph referenced service information at the FAA,
fatigue cracking in a Model MD–88 rear spar (i)(2) of this AD. All applicable corrective Transport Airplane Directorate, 1601 Lind
lower cap of the horizontal stabilizer. We are actions must be done before further flight. Avenue SW., Renton, WA. For information
issuing this AD to detect and correct fatigue on the availability of this material at the
cracking in the rear spar lower caps of the (k) Alternative Methods of Compliance FAA, call 425–227–1221.
Lhorne on DSK30JT082PROD with PROPOSALS
horizontal stabilizer, which, paired with (AMOCs)
Issued in Renton, Washington, on August
cracking in adjacent areas, could adversely (1) The Manager, Los Angeles Aircraft 11, 2016.
affect the structural integrity of the airplane. Certification Office (ACO), FAA, has the Paul R. Bernado,
authority to approve AMOCs for this AD, if
(f) Compliance requested using the procedures found in 14 Acting Manager, Transport Airplane
Comply with this AD within the CFR 39.19. In accordance with 14 CFR 39.19, Directorate, Aircraft Certification Service.
compliance times specified, unless already send your request to your principal inspector [FR Doc. 2016–19936 Filed 8–19–16; 8:45 am]
done. or local Flight Standards District Office, as BILLING CODE 4910–13–P
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Document Created: 2018-02-09 11:37:49
Document Modified: 2018-02-09 11:37:49
| 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 October 6, 2016. | |
| Contact | Haytham Alaidy, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5224; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 81 FR 56540 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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