81 FR 93590 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 245 (December 21, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 245 (December 21, 2016)
| Page Range | 93590-93592 | |
| FR Document | 2016-29306 |
[Federal Register Volume 81, Number 245 (Wednesday, December 21, 2016)] [Rules and Regulations] [Pages 93590-93592] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-29306] [[Page 93590]] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-8845; Directorate Identifier 2016-NM-094-AD; Amendment 39-18732; AD 2016-25-06] 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 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 AD was prompted by a report of fatigue cracking in a rear spar lower cap of the horizontal stabilizer. This AD requires 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 AD also provides an optional terminating fatigue life enhancement modification. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 25, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 25, 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- 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 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: 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: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply 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. The NPRM published in the Federal Register on August 22, 2016 (81 FR 56540) (``the NPRM''). The NPRM was prompted by a report of fatigue cracking in a rear spar lower cap of the horizontal stabilizer. The NPRM proposed to 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. The proposed AD also included an optional terminating fatigue life enhancement modification. 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. Comments We gave the public the opportunity to participate in developing this AD. We have considered the comment received. Boeing supported the NPRM. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD as proposed, except for 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. 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 corrective actions. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 395 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Inspection....................... 3 work-hours x $85 per $0 $255 per $100,725 per hour = $255 per inspection inspection inspection cycle. cycle cycle. ---------------------------------------------------------------------------------------------------------------- [[Page 93591]] 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 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 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 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. 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): 2016-25-06 The Boeing Company: Amendment 39-18732; Docket No. FAA- 2016-8845; Directorate Identifier 2016-NM-094-AD. (a) Effective Date This AD is effective January 25, 2017. (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 8, 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, [[Page 93592]] 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) 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 For more information about this AD, contact Haytham Alaidy, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627- 5224; fax: 562-627-5210; email: [email protected]. (m) 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 Alert Service Bulletin MD80-55A072, dated April 8, 2016. (ii) Reserved. (3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; telephone: 562-797-1717; Internet: https://www.myboeingfleet.com. (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 November 25, 2016. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-29306 Filed 12-20-16; 8:45 am] BILLING CODE 4910-13-P
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DEPARTMENT OF TRANSPORTATION the availability of this material at the inspections, and corrective actions if
FAA, call 425–227–1221. It is also necessary. The proposed AD also
Federal Aviation Administration available on the Internet at http:// included an optional terminating fatigue
www.regulations.gov by searching for life enhancement modification. We are
14 CFR Part 39 and locating Docket No. FAA–2016– issuing this AD to detect and correct
8845. fatigue cracking in the rear spar lower
[Docket No. FAA–2016–8845; Directorate
Identifier 2016–NM–094–AD; Amendment Examining the AD Docket caps of the horizontal stabilizer, which,
39–18732; AD 2016–25–06] paired with cracking in adjacent areas,
You may examine the AD docket on could adversely affect the structural
RIN 2120–AA64 the Internet at http:// integrity of the airplane.
www.regulations.gov by searching for
Airworthiness Directives; The Boeing and locating Docket No. FAA–2016– Comments
Company Airplanes 8845 or in person at the Docket We gave the public the opportunity to
AGENCY: Federal Aviation Management Facility between 9 a.m. participate in developing this AD. We
and 5 p.m., Monday through Friday, have considered the comment received.
Administration (FAA), DOT.
except Federal holidays. The AD docket Boeing supported the NPRM.
ACTION: Final rule. contains this AD, the regulatory
evaluation, any comments received, and Conclusion
SUMMARY: We are adopting a new
airworthiness directive (AD) for all The other information. The address for the We reviewed the relevant data,
Boeing Company Model DC–9–81 (MD– Docket Office (phone: 800–647–5527) is considered the comment received, and
81), DC–9–82 (MD–82), DC–9–83 (MD– Docket Management Facility, U.S. determined that air safety and the
Department of Transportation, Docket public interest require adopting this AD
83), and DC–9–87 (MD–87) airplanes;
Operations, M–30, West Building as proposed, except for minor editorial
and Model MD–88 airplanes. This AD
Ground Floor, Room W12–140, 1200
was prompted by a report of fatigue changes. We have determined that these
New Jersey Avenue SE., Washington,
cracking in a rear spar lower cap of the minor changes:
DC 20590.
horizontal stabilizer. This AD requires • Are consistent with the intent that
repetitive inspections for cracking of the FOR FURTHER INFORMATION CONTACT:
was proposed in the NPRM for
rear spar lower caps of the horizontal Haytham Alaidy, Aerospace Engineer,
correcting the unsafe condition; and
stabilizer, post-modification and post- Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office • Do not add any additional burden
repair inspections, and corrective upon the public than was already
actions if necessary. This AD also (ACO), 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: proposed in the NPRM.
provides an optional terminating fatigue
life enhancement modification. We are 562–627–5224; fax: 562–627–5210; Related Service Information Under 1
issuing this AD to address the unsafe email: haytham.alaidy@faa.gov. CFR Part 51
condition on these products. SUPPLEMENTARY INFORMATION:
We reviewed Boeing Alert Service
DATES: This AD is effective January 25, Discussion Bulletin MD80–55A072, dated April 8,
2017. We issued a notice of proposed 2016. The service information describes
The Director of the Federal Register rulemaking (NPRM) to amend 14 CFR procedures for doing inspections for
approved the incorporation by reference part 39 by adding an AD that would cracking of the rear spar lower caps of
of a certain publication listed in this AD apply to all The Boeing Company Model the horizontal stabilizer, post-
as of January 25, 2017. DC–9–81 (MD–81), DC–9–82 (MD–82), modification and post-repair
ADDRESSES: For service information DC–9–83 (MD–83), and DC–9–87 (MD– inspections, and corrective actions. This
identified in this final rule, contact 87) airplanes; and Model MD–88 service information is reasonably
Boeing Commercial Airplanes, airplanes. The NPRM published in the available because the interested parties
Attention: Contractual & Data Services Federal Register on August 22, 2016 (81 have access to it through their normal
(C&DS), 2600 Westminster Blvd., MC FR 56540) (‘‘the NPRM’’). The NPRM course of business or by the means
110–SK57, Seal Beach, CA 90740–5600; was prompted by a report of fatigue identified in the ADDRESSES section.
telephone: 562–797–1717; Internet: cracking in a rear spar lower cap of the Costs of Compliance
https://www.myboeingfleet.com. You horizontal stabilizer. The NPRM
may view this referenced service proposed to require repetitive We estimate that this AD affects 395
information at the FAA, Transport inspections for cracking of the rear spar airplanes of U.S. registry.
Airplane Directorate, 1601 Lind Avenue lower caps of the horizontal stabilizer, We estimate the following costs to
SW., Renton, WA. For information on post-modification and post-repair comply with this AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Inspection ................... 3 work-hours × $85 per hour = $255 per inspection cycle ................ $0 $255 per $100,725 per
asabaliauskas on DSK3SPTVN1PROD with RULES
inspection inspection
cycle cycle.
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ESTIMATED COSTS FOR OPTIONAL ACTIONS
Cost per
Action Labor cost Parts cost product
Modification .............. 59 work-hours × $85 per hour = $5,015 per stabilizer ............................. $1,267 $6,282 per stabilizer.
We estimate the following costs to do be required based on the results of the determining the number of aircraft that
any necessary replacement that would inspection. We have no way of might need this replacement:
ON-CONDITION COSTS
Action Labor cost Parts cost Cost per product
Replacement ............ 368 work-hours × $85 per hour = $31,280 per stabilizer ......................... $31,408 $62,688 per stabilizer.
We have received no definitive data (4) Will not have a significant issuing this AD to detect and correct fatigue
that would enable us to provide cost economic impact, positive or negative, cracking in the rear spar lower caps of the
estimates for the on-condition actions on a substantial number of small entities horizontal stabilizer, which, paired with
cracking in adjacent areas, could adversely
that require repair using a method under the criteria of the Regulatory
affect the structural integrity of the airplane.
specified in paragraph (k) of this AD. Flexibility Act.
(f) Compliance
Authority for This Rulemaking List of Subjects in 14 CFR Part 39
Comply with this AD within the
Title 49 of the United States Code Air transportation, Aircraft, Aviation compliance times specified, unless already
specifies the FAA’s authority to issue safety, Incorporation by reference, done.
rules on aviation safety. Subtitle I, Safety. (g) Repetitive Inspections and Corrective
section 106, describes the authority of Adoption of the Amendment Actions
the FAA Administrator. Subtitle VII: Except as specified in paragraph (i)(1) of
Aviation Programs, describes in more Accordingly, under the authority
this AD, at the applicable time specified in
detail the scope of the Agency’s delegated to me by the Administrator,
paragraph 1.E., ‘‘Compliance,’’ of Boeing
authority. the FAA amends 14 CFR part 39 as Alert Service Bulletin MD80–55A072, dated
follows: April 8, 2016: Do an open hole high
We are issuing this rulemaking under
frequency eddy current inspection (HFEC) or
the authority described in Subtitle VII, PART 39—AIRWORTHINESS surface HFEC inspection for cracking of the
Part A, Subpart III, Section 44701: DIRECTIVES rear spar lower caps of the horizontal
‘‘General requirements.’’ Under that stabilizer, and do all applicable corrective
section, Congress charges the FAA with ■ 1. The authority citation for part 39 actions; in accordance with the
promoting safe flight of civil aircraft in continues to read as follows: Accomplishment Instructions of Boeing Alert
air commerce by prescribing regulations Authority: 49 U.S.C. 106(g), 40113, 44701. Service Bulletin MD80–55A072, dated April
for practices, methods, and procedures 8, 2016, except as specified in paragraph
the Administrator finds necessary for § 39.13 [Amended] (i)(2) of this AD. Do all applicable corrective
actions before further flight. Repeat the
safety in air commerce. This regulation ■ 2. The FAA amends § 39.13 by adding inspection thereafter at the applicable
is within the scope of that authority the following new airworthiness interval specified in paragraph 1.E.,
because it addresses an unsafe condition directive (AD): ‘‘Compliance,’’ of Boeing Alert Service
that is likely to exist or develop on Bulletin MD80–55A072, dated April 8, 2016,
2016–25–06 The Boeing Company:
products identified in this rulemaking Amendment 39–18732; Docket No. until accomplishment of the actions provided
action. FAA–2016–8845; Directorate Identifier by paragraph (h) of this AD.
Regulatory Findings 2016–NM–094–AD. (h) Optional Terminating Action
(a) Effective Date Accomplishment of the fatigue life
This AD will not have federalism
This AD is effective January 25, 2017. enhancement modification in accordance
implications under Executive Order with the Accomplishment Instructions of
13132. This AD will not have a (b) Affected ADs Boeing Alert Service Bulletin MD80–55A072,
substantial direct effect on the States, on None. dated April 8, 2016, terminates the repetitive
the relationship between the national inspections required by paragraph (g) of this
government and the States, or on the (c) Applicability AD.
distribution of power and This AD applies to all The Boeing (i) Service Information Exceptions
responsibilities among the various Company Model DC–9–81 (MD–81), DC–9–
82 (MD–82), DC–9–83 (MD–83), and DC–9– (1) Where paragraph 1.E., ‘‘Compliance,’’ of
levels of government.
87 (MD–87) airplanes; and Model MD–88 Boeing Alert Service Bulletin MD80–55A072,
For the reasons discussed above, I dated April 8, 2016, specifies a compliance
airplanes; certificated in any category.
certify that this AD:
asabaliauskas on DSK3SPTVN1PROD with RULES
time ‘‘after the original issue date of this
(1) Is not a ‘‘significant regulatory (d) Subject service bulletin,’’ this AD requires
action’’ under Executive Order 12866, Air Transport Association (ATA) of compliance within the specified compliance
(2) Is not a ‘‘significant rule’’ under America Code 55, Stabilizers. time after the effective date of this AD.
(2) If any cracking is found during any
DOT Regulatory Policies and Procedures (e) Unsafe Condition inspection required by this AD, and Boeing
(44 FR 11034, February 26, 1979), This AD was prompted by a report of Alert Service Bulletin MD80–55A072, dated
(3) Will not affect intrastate aviation fatigue cracking in a Model MD–88 rear spar April 8, 2016, specifies to contact Boeing for
in Alaska, and lower cap of the horizontal stabilizer. We are appropriate action: Before further flight,
VerDate Sep<11>2014 17:05 Dec 20, 2016 Jkt 241001 PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 E:\FR\FM\21DER1.SGM 21DER1](https://thefederalregister.org/doc/81_FR_93835/page/2.svg)
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repair the cracking using a method approved (l) Related Information (Regional Jet Series 1000) airplanes.
in accordance with the procedures specified For more information about this AD, This AD was prompted by reports of
in paragraph (k) of this AD. contact Haytham Alaidy, Aerospace two cases where the main landing gear
(j) Post-Modification and Post-Repair Engineer, Airframe Branch, ANM–120L, (MLG) failed to fully extend; it was
Actions FAA, Los Angeles ACO, 3960 Paramount determined that interference between
Boulevard, Lakewood, CA 90712–4137; the MLG door and the MLG fairing seal
For airplanes on which any modification or
phone: 562–627–5224; fax: 562–627–5210; prevented the MLG door from opening
repair specified in (g) or (h) of this AD has
email: haytham.alaidy@faa.gov.
been done: At the applicable time and fully. This AD requires repetitive
intervals specified in paragraph 1.E., (m) Material Incorporated by Reference inspections of the MLG fairing, fairing
‘‘Compliance,’’ of Boeing Alert Service (1) The Director of the Federal Register seal, door, and adjacent structures; and
Bulletin MD80–55A072, dated April 8, 2016, approved the incorporation by reference replacement or repair of affected parts
do all applicable post-modification and post- (IBR) of the service information listed in this and fasteners, or removal of the MLG
repair inspections and all applicable paragraph under 5 U.S.C. 552(a) and 1 CFR door, if necessary. This AD also requires
corrective actions; in accordance with the part 51.
Accomplishment Instructions of Boeing Alert installation of a safety guide in the MLG
(2) You must use this service information fairing and an increase of the spacing
Service Bulletin MD80–55A072, dated April as applicable to do the actions required by
8, 2016; except as specified in paragraph between the MLG door and the fairing,
this AD, unless the AD specifies otherwise.
(i)(2) of this AD. All applicable corrective (i) Boeing Alert Service Bulletin MD80– which would terminate the repetitive
actions must be done before further flight. 55A072, dated April 8, 2016. inspections. We are issuing this AD to
(k) Alternative Methods of Compliance (ii) Reserved. address the unsafe condition on these
(AMOCs) (3) For Boeing service information products.
identified in this AD, contact Boeing DATES: This AD is effective January 25,
(1) The Manager, Los Angeles Aircraft
Commercial Airplanes, Attention:
Certification Office (ACO), FAA, has the 2017.
Contractual & Data Services (C&DS), 2600
authority to approve AMOCs for this AD, if
Westminster Blvd., MC 110–SK57, Seal
The Director of the Federal Register
requested using the procedures found in 14
Beach, CA 90740–5600; telephone: 562–797– approved the incorporation by reference
CFR 39.19. In accordance with 14 CFR 39.19, of certain publications listed in this AD
1717; Internet: https://
send your request to your principal inspector as of January 25, 2017.
www.myboeingfleet.com.
or local Flight Standards District Office, as
(4) You may view this service information ADDRESSES: For service information
appropriate. If sending information directly
at the FAA, Transport Airplane Directorate, identified in this final rule, contact
to the manager of the ACO, send it to the
1601 Lind Avenue SW., Renton, WA. For Bombardier, Inc., 400 Côte-Vertu Road
attention of the person identified in
information on the availability of this West, Dorval, Québec H4S 1Y9, Canada;
paragraph (l) of this AD. Information may be
material at the FAA, call 425–227–1221.
emailed to: 9-ANM-LAACO-AMOC-
(5) You may view this service information
Widebody Customer Response Center
Requests@faa.gov. North America toll-free telephone 1–
that is incorporated by reference at the
(2) Before using any approved AMOC, 866–538–1247 or direct-dial telephone
National Archives and Records
notify your appropriate principal inspector, 1–514–855–2999; fax 514–855–7401;
Administration (NARA). For information on
or lacking a principal inspector, the manager email ac.yul@aero.bombardier.com;
the availability of this material at NARA, call
of the local flight standards district office/
202–741–6030, or go to: http:// Internet http://www.bombardier.com.
certificate holding district office.
www.archives.gov/federal-register/cfr/ibr- You may view this referenced service
(3) An AMOC that provides an acceptable
locations.html. information at the FAA, Transport
level of safety may be used for any repair,
modification, or alteration required by this Issued in Renton, Washington, on Airplane Directorate, 1601 Lind Avenue
AD if it is approved by the Boeing November 25, 2016. SW., Renton, WA. For information on
Commercial Airplanes Organization John P. Piccola, Jr., the availability of this material at the
Designation Authorization (ODA) that has Acting Manager, Transport Airplane FAA, call 425–227–1221. It is also
been authorized by the Manager, Los Angeles Directorate, Aircraft Certification Service. available on the Internet at http://
ACO, to make those findings. To be www.regulations.gov by searching for
[FR Doc. 2016–29306 Filed 12–20–16; 8:45 am]
approved, the repair method, modification
deviation, or alteration deviation must meet BILLING CODE 4910–13–P and locating Docket No. FAA–2016–
the certification basis of the airplane, and the 8847.
approval must specifically refer to this AD. Examining the AD Docket
(4) Except as required by paragraph (i)(2) DEPARTMENT OF TRANSPORTATION
of this AD: For service information that You may examine the AD docket on
contains steps that are labeled as Required Federal Aviation Administration the Internet at http://
for Compliance (RC), the provisions of www.regulations.gov by searching for
paragraphs (k)(4)(i) and (k)(4)(ii) of this AD 14 CFR Part 39 and locating Docket No. FAA–2016–
apply. 8847; or in person at the Docket
(i) The steps labeled as RC, including [Docket No. FAA–2016–8847; Directorate
Identifier 2016–NM–020–AD; Amendment
Management Facility between 9 a.m.
substeps under an RC step and any figures and 5 p.m., Monday through Friday,
identified in an RC step, must be done to 39–18742; AD 2016–25–16]
comply with the AD. If a step or sub-step is
except Federal holidays. The AD docket
RIN 2120–AA64 contains this AD, the regulatory
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or evaluation, any comments received, and
Airworthiness Directives; Bombardier, other information. The street address for
sub-step. An AMOC is required for any
deviations to RC steps, including substeps
Inc. Airplanes the Docket Office (telephone 800–647–
asabaliauskas on DSK3SPTVN1PROD with RULES
and identified figures. AGENCY: Federal Aviation 5527) is Docket Management Facility,
(ii) Steps not labeled as RC may be Administration (FAA), Department of U.S. Department of Transportation,
deviated from using accepted methods in Docket Operations, M–30, West
accordance with the operator’s maintenance
Transportation (DOT).
ACTION: Final rule.
Building Ground Floor, Room W12–140,
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
1200 New Jersey Avenue SE.,
including substeps and identified figures, can SUMMARY: We are adopting a new Washington, DC 20590.
still be done as specified, and the airplane airworthiness directive (AD) for certain FOR FURTHER INFORMATION CONTACT:
can be put back in an airworthy condition. Bombardier, Inc. Model CL–600–2E25 Fabio Buttitta, Aerospace Engineer,
VerDate Sep<11>2014 17:05 Dec 20, 2016 Jkt 241001 PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 E:\FR\FM\21DER1.SGM 21DER1](https://thefederalregister.org/doc/81_FR_93835/page/3.svg)
Document Created: 2018-02-14 09:11:56
Document Modified: 2018-02-14 09:11:56
| 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 January 25, 2017. | |
| 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 93590 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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