81 FR 38897 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 115 (June 15, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 115 (June 15, 2016)
| Page Range | 38897-38901 | |
| FR Document | 2016-13741 |
[Federal Register Volume 81, Number 115 (Wednesday, June 15, 2016)] [Rules and Regulations] [Pages 38897-38901] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-13741] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3635; Directorate Identifier 2015-NM-037-AD; Amendment 39-18553; AD 2016-12-04] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for all Airbus Model A318 series airplanes; A319 series airplanes; A320-211, - 212, -214, -231, -232, and -233 airplanes; and A321 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain structural repair manual (SRM) inspection requirements for the fuselage skin repairs are insufficient to detect cracks. This AD requires an inspection to determine whether any fuselage external skin (doubler) repairs have been accomplished, an inspection for cracking of certain repaired external fuselage skin areas in the fuselage, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin, which could result in reduced structural integrity of the airplane. DATES: This AD becomes effective July 20, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 20, 2016. ADDRESSES: For service information identified in this final rule, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 3635. Examining the AD Docket You may examine the AD docket on the Internet at http:// [[Page 38898]] www.regulations.gov by searching for and locating Docket No. FAA-2015- 3635; 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 street address for the Docket Office (telephone 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. 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 Airbus Model A318 series airplanes; A319 series airplanes; A320-211, -212, -214, -231, - 232, and -233 airplanes; and A321 series airplanes. The NPRM published in the Federal Register on September 28, 2015 (80 FR 58226) (``the NPRM''). The NPRM was prompted by an evaluation by the DAH indicating that the fuselage skin repairs are subject to WFD. The NPRM proposed to require an inspection to determine whether any fuselage external skin (doubler) repairs have been accomplished, an inspection for cracking of certain repaired external fuselage skin areas in the fuselage, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin, which could result in reduced structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015-0036R1, dated March 31, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition on all Airbus Model A318 series airplanes; A319 series airplanes; A320-211, -212, -214, -231, - 232, and -233 airplanes, and A321 series airplanes. The MCAI states: During A320 family Extended Service Goal full scale fatigue tests, it was demonstrated that the inspection thresholds defined in the current Structural Repair Manual (SRM) for the A320 family skin repairs are insufficient to detect possible cracks becoming after repairs. The findings are limited to 1.2 [millimeter] (mm) fuselage skin and cover for all cut-out external repairs. The internal repairs are not affected. This condition, if not detected and corrected, could affect the structural integrity of the fuselage at the repaired skin area(s). To address this potential unsafe condition, Airbus issued Alert Operators Transmission (AOT) A53N007-14 to provide inspection instructions. For the reasons described above, EASA issued AD 2015-0036 [http://www.casa.gov.au/scripts/nc.dll?WCMS:OLDASSET::svPath=/ADFiles/over/a320/,svFileName=2015-0036.pdf] to require a one-time inspection of the affected areas and, depending on findings, accomplishment of applicable repair instructions. Since that [EASA] AD was issued, operators have questioned the inspection threshold for A318 aeroplanes (not yet in the Airbus AOT), which is actually identical to that for A319 aeroplanes. In addition, an error has been detected in paragraph (1) [of the EASA AD], since external doublers may have been installed in the affected area by a modification that may not be recorded as repair. Such doubler installations are also subject to the inspection requirements of this [EASA] AD, which is therefore revised to provide clarifications, correcting paragraph (1) [of the EASA AD] and introducing a Note. Required actions include an inspection to determine whether any fuselage external skin (doubler) repairs have been accomplished, an external ultrasonic inspection or an internal low/high frequency eddy current inspection for cracking of certain repaired external fuselage skin areas in the fuselage, and repair if necessary. The compliance times vary depending on airplane configuration. The earliest compliance time is within 25,200 flight cycles since last repair, or within 350 flight cycles after the effective date of the AD, whichever occurs later. The latest compliance time is within 45,000 flight cycles since last repair; within 1,500 flight cycles from the effective date of the AD, without exceeding 49,100 flight cycles since last repair; or within 350 flight cycles since the effective date of the AD; whichever occurs latest. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-3635. Comments We gave the public the opportunity to participate in developing this AD. We have considered the comments received. The following presents the comments received on the NPRM and the FAA's response to each comment. Support for the NPRM Mr. Bryant Kerr stated that the NPRM is an excellent idea, and it is always worth improving safety on airplanes. Request To Revise Applicability United Airlines (UAL) requested that we revise the NPRM applicability to apply only to airplanes having repairs that were completed before May 1, 2015, the date of the revised service repair manual (SRM). UAL stated that any new airplane deliveries or external repairs accomplished after the updated SRM thresholds will presumably have the correct thresholds contained in the maintenance/inspection program. We partially agree with UAL's request. We agree that airplanes with repairs accomplished using the updated SRM will be in compliance with certain sections of this AD, such as the timescale for the inspection, which is a subset of the AD requirements. However, the SRM update will not replace the remaining AD requirements, which must be applicable to all airplanes identified in paragraph (c) of this AD. We have not changed this AD in this regard. Request To Exclude Inspected Airplanes Delta Airlines (DAL) stated that since certain repairs and modifications on its airplanes have already had their first inspection prior to the compliance time specified in the NPRM, the NPRM requirements should not apply. DAL also stated that if an operator's maintenance/inspection program is more stringent than the requirements of paragraph (m) of the proposed AD, the operator should be excluded from the NPRM requirements. We disagree with DAL's request. Accomplishment of the first inspection is only part of the actions required by this AD. Paragraph (m) of this AD requires revision of the post-repair inspection threshold(s) in the operator's maintenance program or inspection program. This AD includes the minimum requirements for mitigating the identified unsafe condition. However, under the provisions of paragraph (n)(1) of this AD, we will consider requests for approval of different methods of compliance if sufficient data are submitted to substantiate that the change would provide an acceptable level of safety. We have not changed this AD in this regard. Request To Revise Compliance Time DAL requested a compliance time extension from 350 flight cycles to 6 months. DAL stated that depending on [[Page 38899]] the fleet utilization, an operator of a large, older fleet could be required to accomplish the compliance rework within a few months, thereby creating a significant impact on its available resources. DAL also stated that it is possible that several airplanes will be grounded because it may not have enough resources to comply with the 350-flight- cycle limit. We do not agree with DAL's request. DAL's rationale for a compliance time extension does not provide an acceptable level of safety. The compliance time of this AD is based on a risk assessment. Some safety issues are more time sensitive than others. We have considered the compliance time established by EASA, and the overall risk to the fleet, including the severity of the identified unsafe condition and the likelihood of the occurrence of the unsafe condition, to determine the compliance time. However, under the provisions of paragraph (n)(1) of this AD, operators may apply for an extension of the compliance time by providing a satisfactory rationale explaining why a compliance time extension provides an acceptable level of safety. We have not changed this final rule in this regard. Request To Clarify Requirements and Approve Certain Repair Information Sources DAL requested that we make a distinction that the NPRM requirements apply only to external repair fasteners common to the 1.2-millimeter (mm) skin. DAL also stated that we should approve category B repairs done using the latest revision of the SRM and any repair design approval sheet (RDAS) approved after July 1, 2014. DAL stated that the applicable Airbus SRM repair inspection thresholds have been revised this year to address certain inadequacies. We do not agree with DAL's requests. Paragraph (g) of this AD already requires an inspection to determine whether any fuselage doubler repairs have been accomplished on affected fuselage sections with a skin thickness of 1.2 mm. DAL did not substantiate how the corrective actions in any RDAS for category ``B'' repairs approved after July 1, 2014, and the latest revision of the SRMs would adequately address the unsafe condition. However, the commenter may use the provisions of paragraph (n)(2) of this AD for obtaining corrective actions from a manufacturer. We have not changed this AD in this regard. Request To Clarify Inspection Timeframes UAL requested clarification on how the NPRM addresses detection of cracking in the timeframe between the inspection threshold specified in the NPRM and Airbus Alert Operators Transmission A53N007-14, dated July 22, 2014, and the repetitive inspections specified in the SRM. UAL stated that the compliance time has a short threshold if the repair records are inconclusive, which is as early as 350 flight cycles from the effective date of the AD; therefore, the initial inspection could be accomplished much earlier than the crack detection period. We agree to clarify the inspection timeframes. The 350-flight-cycle compliance time is a second option to the compliance time specified in Airbus Alert Operators Transmission A53N007-14, dated July 22, 2014. The compliance time is based on a risk assessment that takes into consideration the fatigue crack length propagation. We have considered the compliance time established by EASA, and the overall risk to the fleet, including the severity of the identified unsafe condition and the likelihood of the occurrence of the unsafe condition. No change to the AD is necessary in this regard. Request To Correct Non-Destructive Testing Manual (NTM) Task Numbers DAL stated that Airbus Alert Operators Transmission A53N007-14, dated July 22, 2014, references incorrect formatting of NTM task numbers. DAL stated the formatting should be ``51-10-15-270-801-A01'' and ``51-10-16-250-801-A01,'' and not ``51-10-15-270-801-A-01'' and ``51-10-16-250-801-A-01.'' We disagree with DAL's statement. NTM task numbers 51-10-15-270- 801-A-01 and 51-10-16-250-801-A-01 are correctly referenced in Airbus Alert Operators Transmission A53N007-14, dated July 22, 2014, and in the Airbus A318/319/320/321 Non-Destructive Testing Manual. We have not changed this AD in this regard. Clarification of Unsafe Condition Language We revised the description of the precipitating event in the SUMMARY and paragraph (e) of this AD to correspond to the wording used in the MCAI AD. Conclusion We reviewed the relevant data, considered the comments 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. 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 Airbus has issued Alert Operators Transmission A53N007-14, dated July 22, 2014. The service information describes procedures for an inspection to detect cracking on repaired 1.2-millimeter fuselage skin areas on fuselage sections 11, 12, 13, 14, 16, and 17 at external doubler 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. Costs of Compliance We estimate that this AD affects 940 airplanes of U.S. registry. We also estimate that it will take about 2 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $159,800, or $170 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in 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. [[Page 38900]] Regulatory Findings We determined that 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 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. 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): 2016-12-04 Airbus: Amendment 39-18553. Docket No. FAA-2015-3635; Directorate Identifier 2015-NM-037-AD. (a) Effective Date This AD becomes effective July 20, 2016. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes specified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A318-111, -112, -121, and -122 airplanes. (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes. (3) Airbus Model A320-211, -212, -214, -231, -232, and -233 airplanes. (4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain structural repair manual (SRM) inspection requirements for the fuselage skin repairs are insufficient to detect cracks. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection To Determine Repair Areas At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD: Do an inspection to determine whether any fuselage external skin (doubler) repairs have been accomplished on fuselage sections 11, 12, 13, 14, 16, and 17 with a skin thickness of 1.2 millimeters. A review of airplane maintenance records is acceptable in lieu of this inspection if the identification of applicable repairs can be conclusively determined from that review. (1) For Model A319, A320, and A321 series airplanes: Except as specified in paragraphs (h)(1) and (h)(2) of this AD, at the applicable time specified in paragraphs 4.1.1.b. and 4.1.1.c. of the ``Accomplishment Timescale'' of Airbus Alert Operators Transmission (AOT) A53N007-14, dated July 22, 2014, or within 350 flight cycles after the effective date of this AD, whichever occurs later. (2) For Model A318 series airplanes: Except as specified in paragraphs (h)(1) and (h)(2) of this AD, at the Model A319 airplane time specified in paragraphs 4.1.1.b. and 4.1.1.c. of the ``Accomplishment Timescale'' of Airbus AOT A53N007-14, dated July 22, 2014, or within 350 flight cycles after the effective date of this AD, whichever occurs later. (h) Exceptions to Service Information (1) Where paragraphs 4.1.1.b. and 4.1.1.c. of the ``Accomplishment Timescale'' of Airbus AOT A53N007-14, dated July 22, 2014, specify ``FC,'' this AD specifies ``flight cycles.'' (2) Where paragraphs 4.1.1.b. and 4.1.1.c. of the ``Accomplishment Timescale'' of Airbus AOT A53N007-14, dated July 22, 2014, specify ``from AOT issuance,'' this AD specifies ``as of the effective date of this AD.'' (i) Inspection for Cracking If, during the inspection required by paragraph (g) of this AD, it is determined that any fuselage external skin (doubler) repair has been accomplished on fuselage section 11, 12, 13, 14, 16, or 17: At the applicable time specified paragraph (g)(1) or (g)(2) of this AD, do an external ultrasonic inspection or an internal low frequency eddy current (LFEC) inspection for cracking of all of the repaired 1.2-millimeter (mm) fuselage skin areas, in accordance with the instructions specified in paragraph 4.2.2, ``Inspection Requirements,'' of Airbus AOT A53N007-14, dated July 22, 2014, except as provided by paragraph (j) of this AD. (j) Optional Inspection for Cracking As an optional method of compliance to the ultrasonic inspection or LFEC inspection required by paragraph (i) of this AD: Do a high frequency eddy current (HFEC) inspection for cracking in the cut-out surrounding the fastener area, at and in front (approximately 10-15 millimeters) of the fastener row, after doubler removal and before any new extended doubler installation, using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (k) Optional Repetitive Inspections In lieu of doing the inspection required by paragraph (i) of this AD: Within the applicable compliance time specified in paragraph 4.1.1, ``Accomplishment Timescale,'' of Airbus AOT A53N007-14, dated July 22, 2014, after accomplishing the inspections required by paragraph (g) of this AD, do a detailed inspection or HFEC inspection and repeat the inspection thereafter within the applicable compliance times specified in paragraph 4.1.1, ``Accomplishment Timescale,'' of Airbus AOT A53N007-14, dated July 22, 2014. The inspections must be done in accordance with the instructions of paragraph 4.2.2, ``Inspection Requirements,'' of Airbus AOT A53N007-14, dated July 22, 2014. For Model A318 series airplanes, use the applicable compliance times and instructions specified in Airbus AOT A53N007-14, dated July 22, 2014, that are specified for Model A319 series airplanes. (l) Repair If any crack is found during any inspection required by paragraph (i), (j), or (k) of this AD: Before further flight, repair the cracking, in accordance with the instructions of paragraph 4.2.3, ``Findings,'' of Airbus AOT A53N007-14, dated July 22, 2014, except where Airbus AOT A53N007-14, dated July 22, 2014, specifies to contact Airbus for a repair design approval sheet or for further instructions, this AD requires repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. (m) FAA-Approved Maintenance or Inspection Program Revision Concurrently with the accomplishment of any repair required by paragraph (l) of this AD, revise the post-repair inspection threshold(s) in the applicable FAA-approved maintenance program or inspection program, as applicable, in accordance with the instructions specified in paragraph 4.1.1, ``Accomplishment Timescale,'' of Airbus AOT A53N007-14, dated July 22, 2014; except for Model A318 series airplanes use the instructions specified for Model A319 series airplanes. [[Page 38901]] (n) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-1405; fax 425-227-1149. Information may be emailed to: [email protected]. 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. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015-0036R1, dated March 31, 2015, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-3635. (p) 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 this AD specifies otherwise. (i) Airbus Alert Operators Transmission A53N007-14, dated July 22, 2014. (ii) Reserved. (3) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.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 May 31, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-13741 Filed 6-14-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 115 / Wednesday, June 15, 2016 / Rules and Regulations 38897
As with all Federal promotion For the reasons set forth in the DEPARTMENT OF TRANSPORTATION
programs, reports and forms are preamble, 7 CFR part 1214 is amended
periodically reviewed to reduce as follows: Federal Aviation Administration
information requirements and
duplication by industry and public PART 1214—CHRISTMAS TREE 14 CFR Part 39
sector agencies. Finally, USDA has not PROMOTION, RESEARCH, AND [Docket No. FAA–2015–3635; Directorate
identified any relevant Federal rules INFORMATION ORDER Identifier 2015–NM–037–AD; Amendment
that duplicate, overlap, or conflict with 39–18553; AD 2016–12–04]
this rule. ■ 1. The authority citation for 7 CFR
RIN 2120–AA64
AMS is committed to complying with part 1214 continues to read as follows:
the E-Government Act, to promote the Authority: 7 U.S.C. 7411–7425; 7 U.S.C. Airworthiness Directives; Airbus
use of the Internet and other 7401. Airplanes
information technologies to provide
increased opportunities for citizen ■ 2. Section 1214.5 is revised to read as AGENCY: Federal Aviation
access to Government information and follows: Administration (FAA), Department of
services, and for other purposes. Transportation (DOT).
Regarding outreach efforts, the Board § 1214.5 Crop year. ACTION: Final rule.
met on July 17, 2015, and unanimously Crop year means the period August 1 SUMMARY: We are adopting a new
recommended these changes to the through July 31 or such other period airworthiness directive (AD) for all
Order. All of the Board’s meetings, approved by the Secretary. Airbus Model A318 series airplanes;
including meetings held via A319 series airplanes; A320–211, –212,
teleconference, are open to the public ■ 3. Section 1214.8 is revised to read as
follows: –214, –231, –232, and –233 airplanes;
and interested persons are invited to and A321 series airplanes. This AD was
participate and express their views. prompted by an evaluation by the
§ 1214.8 Fiscal period.
A proposed rule concerning this design approval holder (DAH)
action was published in the Federal Fiscal period means the period indicating that certain structural repair
Register on March 1, 2016 (81 FR August 1 through July 31 or such other manual (SRM) inspection requirements
10530). The proposal was made period approved by the Secretary. for the fuselage skin repairs are
available through the Internet by USDA insufficient to detect cracks. This AD
■ 4. Subpart C, consisting of § 1214.520,
and the Office of the Federal Register. A requires an inspection to determine
is added to read as follows:
15-day comment period ending March whether any fuselage external skin
16, 2016, was provided to allow Subpart C—Provisions Implementing (doubler) repairs have been
interested persons to submit comments. the Christmas Tree Promotion, accomplished, an inspection for
No comments were received. Research, and Information Order cracking of certain repaired external
After consideration of all relevant fuselage skin areas in the fuselage, and
matters presented, including the § 1214.520 Late payment and interest repair if necessary. We are issuing this
information and recommendation charges for past due assessments. AD to detect and correct fatigue
submitted by the Board and other cracking of the fuselage skin, which
(a) A late payment charge shall be
available information, it is hereby found could result in reduced structural
imposed on any producer or importer
that this rule, as hereinafter set forth, is integrity of the airplane.
who fails to make timely remittance to
consistent with and will effectuate the DATES: This AD becomes effective July
the Board of the total assessments for
purposes of the 1996 Act. 20, 2016.
which such producer or importer is
It is further found that good cause The Director of the Federal Register
liable. The late payment charge will be
exists for not postponing the effective approved the incorporation by reference
imposed on any assessments not
date of this rule until 30 days after of a certain publication listed in this AD
received within 30 calendar days of the
publication in the Federal Register (5 as of July 20, 2016.
date they are due. This one-time late
U.S.C. 553) because this is the initial ADDRESSES: For service information
payment charge shall be $250 and will
year for the collection of assessments identified in this final rule, contact
be increased to $500 after 90 days of
under the Order, on the 2015 harvest, Airbus, Airworthiness Office—EIAS, 1
delinquency.
and assessments were due on February Rond Point Maurice Bellonte, 31707
15, 2016. Importers are responsible for (b) In addition to the late payment Blagnac Cedex, France; telephone +33 5
paying assessments directly to the Board charge, 1.5 percent per month interest 61 93 36 96; fax +33 5 61 93 44 51; email
30 calendar days after importation. The on the outstanding balance, including account.airworth-eas@airbus.com;
Board would like to implement this any late payment charge and accrued Internet http://www.airbus.com. You
incentive as soon as possible to facilitate interest, will be added to any accounts may view this referenced service
the initial collection of assessments. for which payment has not been information at the FAA, Transport
Additionally, this action was received by the Board within 30 Airplane Directorate, 1601 Lind Avenue
unanimously recommended by the calendar days after the date the SW., Renton, WA. For information on
Board. Further, a 15-day comment assessments are due. Such interest will the availability of this material at the
period was provided for in the proposed continue to accrue monthly until the FAA, call 425–227–1221. It is also
rule and no comments were received. outstanding balance is paid to the available on the Internet at http://
Board. www.regulations.gov by searching for
ehiers on DSK5VPTVN1PROD with RULES
List of Subjects in 7 CFR Part 1214
Dated: June 10, 2016. and locating Docket No. FAA–2015–
Administrative practice and 3635.
Elanor Starmer,
procedure, Advertising, Consumer
information, Christmas trees, Marketing Administrator. Examining the AD Docket
agreements, Reporting and [FR Doc. 2016–14150 Filed 6–14–16; 8:45 am] You may examine the AD docket on
recordkeeping requirements. BILLING CODE P the Internet at http://
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![38898 Federal Register / Vol. 81, No. 115 / Wednesday, June 15, 2016 / Rules and Regulations
www.regulations.gov by searching for to detect possible cracks becoming after Support for the NPRM
and locating Docket No. FAA–2015– repairs. The findings are limited to 1.2
[millimeter] (mm) fuselage skin and cover for Mr. Bryant Kerr stated that the NPRM
3635; or in person at the Docket is an excellent idea, and it is always
Management Facility between 9 a.m. all cut-out external repairs. The internal
repairs are not affected. worth improving safety on airplanes.
and 5 p.m., Monday through Friday, This condition, if not detected and
except Federal holidays. The AD docket Request To Revise Applicability
corrected, could affect the structural integrity
contains this AD, the regulatory of the fuselage at the repaired skin area(s). United Airlines (UAL) requested that
evaluation, any comments received, and To address this potential unsafe condition, we revise the NPRM applicability to
other information. The street address for Airbus issued Alert Operators Transmission apply only to airplanes having repairs
the Docket Office (telephone 800–647– (AOT) A53N007–14 to provide inspection that were completed before May 1, 2015,
5527) is Docket Management Facility, instructions. the date of the revised service repair
U.S. Department of Transportation, For the reasons described above, EASA manual (SRM). UAL stated that any new
Docket Operations, M–30, West issued AD 2015–0036 [http://
airplane deliveries or external repairs
www.casa.gov.au/scripts/
Building Ground Floor, Room W12–140, nc.dll?WCMS:OLDASSET::svPath=/ADFiles/ accomplished after the updated SRM
1200 New Jersey Avenue SE., over/a320/,svFileName=2015-0036.pdf] to thresholds will presumably have the
Washington, DC 20590. require a one-time inspection of the affected correct thresholds contained in the
FOR FURTHER INFORMATION CONTACT: areas and, depending on findings, maintenance/inspection program.
Sanjay Ralhan, Aerospace Engineer, accomplishment of applicable repair We partially agree with UAL’s
International Branch, ANM–116, instructions. request. We agree that airplanes with
Transport Airplane Directorate, FAA, Since that [EASA] AD was issued, repairs accomplished using the updated
operators have questioned the inspection SRM will be in compliance with certain
1601 Lind Avenue SW., Renton, WA threshold for A318 aeroplanes (not yet in the
98057–3356; telephone 425–227–1405; sections of this AD, such as the
Airbus AOT), which is actually identical to timescale for the inspection, which is a
fax 425–227–1149. that for A319 aeroplanes. In addition, an
error has been detected in paragraph (1) [of
subset of the AD requirements.
SUPPLEMENTARY INFORMATION:
the EASA AD], since external doublers may However, the SRM update will not
Discussion have been installed in the affected area by a replace the remaining AD requirements,
modification that may not be recorded as which must be applicable to all
We issued a notice of proposed
repair. airplanes identified in paragraph (c) of
rulemaking (NPRM) to amend 14 CFR
Such doubler installations are also subject this AD. We have not changed this AD
part 39 by adding an AD that would to the inspection requirements of this [EASA] in this regard.
apply to all Airbus Model A318 series AD, which is therefore revised to provide
airplanes; A319 series airplanes; A320– clarifications, correcting paragraph (1) [of the Request To Exclude Inspected
211, –212, –214, –231, –232, and –233 EASA AD] and introducing a Note. Airplanes
airplanes; and A321 series airplanes. Delta Airlines (DAL) stated that since
The NPRM published in the Federal Required actions include an
certain repairs and modifications on its
Register on September 28, 2015 (80 FR inspection to determine whether any
airplanes have already had their first
58226) (‘‘the NPRM’’). The NPRM was fuselage external skin (doubler) repairs
inspection prior to the compliance time
prompted by an evaluation by the DAH have been accomplished, an external
specified in the NPRM, the NPRM
indicating that the fuselage skin repairs ultrasonic inspection or an internal low/
requirements should not apply. DAL
are subject to WFD. The NPRM high frequency eddy current inspection
also stated that if an operator’s
proposed to require an inspection to for cracking of certain repaired external
maintenance/inspection program is
determine whether any fuselage external fuselage skin areas in the fuselage, and
more stringent than the requirements of
skin (doubler) repairs have been repair if necessary. The compliance paragraph (m) of the proposed AD, the
accomplished, an inspection for times vary depending on airplane operator should be excluded from the
cracking of certain repaired external configuration. The earliest compliance NPRM requirements.
fuselage skin areas in the fuselage, and time is within 25,200 flight cycles since We disagree with DAL’s request.
repair if necessary. We are issuing this last repair, or within 350 flight cycles Accomplishment of the first inspection
AD to detect and correct fatigue after the effective date of the AD, is only part of the actions required by
cracking of the fuselage skin, which whichever occurs later. The latest this AD. Paragraph (m) of this AD
could result in reduced structural compliance time is within 45,000 flight requires revision of the post-repair
integrity of the airplane. cycles since last repair; within 1,500 inspection threshold(s) in the operator’s
The European Aviation Safety Agency flight cycles from the effective date of maintenance program or inspection
(EASA), which is the Technical Agent the AD, without exceeding 49,100 flight program. This AD includes the
for the Member States of the European cycles since last repair; or within 350 minimum requirements for mitigating
Union, has issued EASA Airworthiness flight cycles since the effective date of the identified unsafe condition.
Directive 2015–0036R1, dated March 31, the AD; whichever occurs latest. You However, under the provisions of
2015 (referred to after this as the may examine the MCAI in the AD paragraph (n)(1) of this AD, we will
Mandatory Continuing Airworthiness docket on the Internet at http:// consider requests for approval of
Information, or ‘‘the MCAI’’), to correct www.regulations.gov by searching for different methods of compliance if
an unsafe condition on all Airbus Model and locating Docket No. FAA–2015– sufficient data are submitted to
A318 series airplanes; A319 series 3635. substantiate that the change would
airplanes; A320–211, –212, –214, –231, Comments provide an acceptable level of safety.
–232, and –233 airplanes, and A321 We have not changed this AD in this
ehiers on DSK5VPTVN1PROD with RULES
series airplanes. The MCAI states: We gave the public the opportunity to regard.
During A320 family Extended Service Goal
participate in developing this AD. We
have considered the comments received. Request To Revise Compliance Time
full scale fatigue tests, it was demonstrated
that the inspection thresholds defined in the The following presents the comments DAL requested a compliance time
current Structural Repair Manual (SRM) for received on the NPRM and the FAA’s extension from 350 flight cycles to 6
the A320 family skin repairs are insufficient response to each comment. months. DAL stated that depending on
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![38900 Federal Register / Vol. 81, No. 115 / Wednesday, June 15, 2016 / Rules and Regulations
Regulatory Findings (d) Subject Requirements,’’ of Airbus AOT A53N007–14,
Air Transport Association (ATA) of dated July 22, 2014, except as provided by
We determined that this AD will not paragraph (j) of this AD.
America Code 53, Fuselage.
have federalism implications under
Executive Order 13132. This AD will (e) Reason (j) Optional Inspection for Cracking
not have a substantial direct effect on This AD was prompted by an evaluation by As an optional method of compliance to
the States, on the relationship between the design approval holder (DAH) indicating the ultrasonic inspection or LFEC inspection
the national government and the States, that certain structural repair manual (SRM) required by paragraph (i) of this AD: Do a
or on the distribution of power and inspection requirements for the fuselage skin high frequency eddy current (HFEC)
responsibilities among the various repairs are insufficient to detect cracks. We inspection for cracking in the cut-out
are issuing this AD to detect and correct surrounding the fastener area, at and in front
levels of government.
fatigue cracking of the fuselage skin, which (approximately 10–15 millimeters) of the
For the reasons discussed above, I could result in reduced structural integrity of fastener row, after doubler removal and
certify that this AD: the airplane. before any new extended doubler
1. Is not a ‘‘significant regulatory installation, using a method approved by the
action’’ under Executive Order 12866; (f) Compliance Manager, International Branch, ANM–116,
2. Is not a ‘‘significant rule’’ under the Comply with this AD within the Transport Airplane Directorate, FAA; or the
DOT Regulatory Policies and Procedures compliance times specified, unless already European Aviation Safety Agency (EASA); or
(44 FR 11034, February 26, 1979); done. Airbus’s EASA Design Organization
3. Will not affect intrastate aviation in (g) Inspection To Determine Repair Areas Approval (DOA).
Alaska; and At the applicable time specified in (k) Optional Repetitive Inspections
4. Will not have a significant paragraph (g)(1) or (g)(2) of this AD: Do an In lieu of doing the inspection required by
economic impact, positive or negative, inspection to determine whether any fuselage paragraph (i) of this AD: Within the
on a substantial number of small entities external skin (doubler) repairs have been applicable compliance time specified in
under the criteria of the Regulatory accomplished on fuselage sections 11, 12, 13, paragraph 4.1.1, ‘‘Accomplishment
Flexibility Act. 14, 16, and 17 with a skin thickness of 1.2 Timescale,’’ of Airbus AOT A53N007–14,
millimeters. A review of airplane dated July 22, 2014, after accomplishing the
List of Subjects in 14 CFR Part 39 maintenance records is acceptable in lieu of inspections required by paragraph (g) of this
this inspection if the identification of AD, do a detailed inspection or HFEC
Air transportation, Aircraft, Aviation applicable repairs can be conclusively
safety, Incorporation by reference, inspection and repeat the inspection
determined from that review. thereafter within the applicable compliance
Safety. (1) For Model A319, A320, and A321 series times specified in paragraph 4.1.1,
airplanes: Except as specified in paragraphs
Adoption of the Amendment ‘‘Accomplishment Timescale,’’ of Airbus
(h)(1) and (h)(2) of this AD, at the applicable
AOT A53N007–14, dated July 22, 2014. The
Accordingly, under the authority time specified in paragraphs 4.1.1.b. and
inspections must be done in accordance with
delegated to me by the Administrator, 4.1.1.c. of the ‘‘Accomplishment Timescale’’
the instructions of paragraph 4.2.2,
the FAA amends 14 CFR part 39 as of Airbus Alert Operators Transmission
‘‘Inspection Requirements,’’ of Airbus AOT
follows: (AOT) A53N007–14, dated July 22, 2014, or
within 350 flight cycles after the effective A53N007–14, dated July 22, 2014. For Model
date of this AD, whichever occurs later. A318 series airplanes, use the applicable
PART 39—AIRWORTHINESS compliance times and instructions specified
(2) For Model A318 series airplanes:
DIRECTIVES in Airbus AOT A53N007–14, dated July 22,
Except as specified in paragraphs (h)(1) and
(h)(2) of this AD, at the Model A319 airplane 2014, that are specified for Model A319
■ 1. The authority citation for part 39 time specified in paragraphs 4.1.1.b. and series airplanes.
continues to read as follows: 4.1.1.c. of the ‘‘Accomplishment Timescale’’ (l) Repair
Authority: 49 U.S.C. 106(g), 40113, 44701. of Airbus AOT A53N007–14, dated July 22,
2014, or within 350 flight cycles after the If any crack is found during any inspection
§ 39.13 [Amended] effective date of this AD, whichever occurs required by paragraph (i), (j), or (k) of this
later. AD: Before further flight, repair the cracking,
■ 2. The FAA amends § 39.13 by adding in accordance with the instructions of
the following new airworthiness (h) Exceptions to Service Information paragraph 4.2.3, ‘‘Findings,’’ of Airbus AOT
directive (AD): (1) Where paragraphs 4.1.1.b. and 4.1.1.c. A53N007–14, dated July 22, 2014, except
of the ‘‘Accomplishment Timescale’’ of where Airbus AOT A53N007–14, dated July
2016–12–04 Airbus: Amendment 39–18553.
Docket No. FAA–2015–3635; Directorate Airbus AOT A53N007–14, dated July 22, 22, 2014, specifies to contact Airbus for a
Identifier 2015–NM–037–AD. 2014, specify ‘‘FC,’’ this AD specifies ‘‘flight repair design approval sheet or for further
cycles.’’ instructions, this AD requires repair using a
(a) Effective Date (2) Where paragraphs 4.1.1.b. and 4.1.1.c. method approved by the Manager,
This AD becomes effective July 20, 2016. of the ‘‘Accomplishment Timescale’’ of International Branch, ANM–116, Transport
Airbus AOT A53N007–14, dated July 22, Airplane Directorate, FAA; or the EASA; or
(b) Affected ADs 2014, specify ‘‘from AOT issuance,’’ this AD Airbus’s EASA DOA.
None. specifies ‘‘as of the effective date of this AD.’’ (m) FAA-Approved Maintenance or
(c) Applicability (i) Inspection for Cracking Inspection Program Revision
This AD applies to the Airbus airplanes If, during the inspection required by Concurrently with the accomplishment of
specified in paragraphs (c)(1) through (c)(4) paragraph (g) of this AD, it is determined that any repair required by paragraph (l) of this
of this AD, certificated in any category, all any fuselage external skin (doubler) repair AD, revise the post-repair inspection
manufacturer serial numbers. has been accomplished on fuselage section threshold(s) in the applicable FAA-approved
(1) Airbus Model A318–111, –112, –121, 11, 12, 13, 14, 16, or 17: At the applicable maintenance program or inspection program,
ehiers on DSK5VPTVN1PROD with RULES
and –122 airplanes. time specified paragraph (g)(1) or (g)(2) of as applicable, in accordance with the
(2) Airbus Model A319–111, –112, –113, this AD, do an external ultrasonic inspection instructions specified in paragraph 4.1.1,
–114, –115, –131, –132, and –133 airplanes. or an internal low frequency eddy current ‘‘Accomplishment Timescale,’’ of Airbus
(3) Airbus Model A320–211, –212, –214, (LFEC) inspection for cracking of all of the AOT A53N007–14, dated July 22, 2014;
–231, –232, and –233 airplanes. repaired 1.2-millimeter (mm) fuselage skin except for Model A318 series airplanes use
(4) Airbus Model A321–111, –112, –131, areas, in accordance with the instructions the instructions specified for Model A319
–211, –212, –213, –231, and –232 airplanes. specified in paragraph 4.2.2, ‘‘Inspection series airplanes.
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![Federal Register / Vol. 81, No. 115 / Wednesday, June 15, 2016 / Rules and Regulations 38901
(n) Other FAA AD Provisions www.archives.gov/federal-register/cfr/ibr- For service information identified in
The following provisions also apply to this locations.html. this AD, contact GROB Aircraft AG,
AD: Issued in Renton, Washington, on May 31, Product Support, Lettenbachstrasse 9,
(1) Alternative Methods of Compliance 2016. D–86874 Tussenhausen-Mattsies,
(AMOCs): The Manager, International Michael Kaszycki, Germany, telephone: + 49 (0) 8268–998–
Branch, ANM–116, Transport Airplane 105; fax: + 49 (0) 8268–998–200; email:
Acting Manager, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
Directorate, Aircraft Certification Service. productsupport@grob-aircraft.com;
using the procedures found in 14 CFR 39.19. [FR Doc. 2016–13741 Filed 6–14–16; 8:45 am] Internet: grob-aircraft.com. You may
In accordance with 14 CFR 39.19, send your BILLING CODE 4910–13–P review copies of the referenced service
request to your principal inspector or local information at the FAA, Small Airplane
Flight Standards District Office, as Directorate, 901 Locust, Kansas City,
appropriate. If sending information directly DEPARTMENT OF TRANSPORTATION Missouri 64106. For information on the
to the International Branch, send it to ATTN: availability of this material at the FAA,
Sanjay Ralhan, Aerospace Engineer, Federal Aviation Administration call (816) 329–4148. It is also available
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
on the Internet at http://
14 CFR Part 39 www.regulations.gov by searching for
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149. [Docket No. FAA–2016–7057; Directorate locating Docket No. FAA–2016–7057.
Information may be emailed to: 9-ANM-116- Identifier 2016–CE–017–AD; Amendment
Examining the AD Docket
AMOC-REQUESTS@faa.gov. Before using 39–18557; AD 2016–12–08]
any approved AMOC, notify your appropriate You may examine the AD docket on
principal inspector, or lacking a principal RIN 2120–AA64
the Internet at http://
inspector, the manager of the local flight www.regulations.gov by searching for
standards district office/certificate holding Airworthiness Directives; GROB
Aircraft AG Airplanes and locating Docket No. FAA–2016–
district office.
(2) Contacting the Manufacturer: For any
7057; or in person at the Docket
AGENCY: Federal Aviation Management Facility between 9 a.m.
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
Administration (FAA), DOT. and 5 p.m., Monday through Friday,
be accomplished using a method approved ACTION: Final rule; request for except Federal holidays. The AD docket
by the Manager, International Branch, ANM– comments. contains this AD, the regulatory
116, Transport Airplane Directorate, FAA; or evaluation, any comments received, and
the EASA; or Airbus’s EASA DOA. If SUMMARY: We are adopting a new
other information. The street address for
approved by the DOA, the approval must airworthiness directive (AD) for GROB
the Docket Office (telephone (800) 647–
include the DOA-authorized signature. Aircraft AG Model G115EG airplanes.
5527) is in the ADDRESSES section.
This AD results from mandatory
(o) Related Information Comments will be available in the AD
continuing airworthiness information
(1) Refer to Mandatory Continuing docket shortly after receipt.
(MCAI) issued by the aviation authority
Airworthiness Information (MCAI) EASA FOR FURTHER INFORMATION CONTACT: Karl
Airworthiness Directive 2015–0036R1, dated
of another country to identify and
correct an unsafe condition on an Schletzbaum, Aerospace Engineer, FAA,
March 31, 2015, for related information. This Small Airplane Directorate, 901 Locust,
MCAI may be found in the AD docket on the aviation product. The MCAI describes
Internet at http://www.regulations.gov by the unsafe condition as cracks in the Room 301, Kansas City, Missouri 64106;
searching for and locating Docket No. FAA– bonded joint of the rear horizontal telephone: (816) 329–4123; fax: (816)
2015–3635. stabilizer frame. We are issuing this AD 329–4090; email: karl.schletzbaum@
to require actions to address the unsafe faa.gov.
(p) Material Incorporated by Reference
condition on these products. SUPPLEMENTARY INFORMATION:
(1) The Director of the Federal Register
approved the incorporation by reference DATES: This AD is effective July 20,
Discussion
(IBR) of the service information listed in this 2016.
paragraph under 5 U.S.C. 552(a) and 1 CFR The Director of the Federal Register The European Aviation Safety Agency
part 51. approved the incorporation by reference (EASA), which is the Technical Agent
(2) You must use this service information of a certain publication listed in the AD for the Member States of the European
as applicable to do the actions required by as of July 20, 2016. Community, has issued EASA AD No.:
this AD, unless this AD specifies otherwise. We must receive comments on this 2016–0091, dated May 16, 2016
(i) Airbus Alert Operators Transmission AD by August 1, 2016. (referred to after this as ‘‘the MCAI’’), to
A53N007–14, dated July 22, 2014.
ADDRESSES: You may send comments by correct an unsafe condition for the
(ii) Reserved.
(3) For service information identified in any of the following methods: specified products. The MCAI states:
this AD, contact Airbus, Airworthiness • Federal eRulemaking Portal: Go to Cracks were found in the bonded joint of
Office—EIAS, 1 Rond Point Maurice http://www.regulations.gov. Follow the the rear horizontal stabiliser frame of G 115E
Bellonte, 31707 Blagnac Cedex, France; instructions for submitting comments. aeroplanes.
telephone +33 5 61 93 36 96; fax +33 5 61 • Fax: (202) 493–2251. This condition, if not detected and
93 44 51; email account.airworth-eas@ • Mail: U.S. Department of corrected, may lead to crack propagation into
airbus.com; Internet http://www.airbus.com. Transportation, Docket Operations, M– primary structural elements, with
(4) You may view this service information 30, West Building Ground Floor, Room detrimental effect on the structural integrity
at the FAA, Transport Airplane Directorate, W12–140, 1200 New Jersey Avenue SE., of the aeroplane.
1601 Lind Avenue SW., Renton, WA. For Washington, DC 20590. To address this potential unsafe condition,
information on the availability of this • Hand Delivery: U.S. Department of GROB issued Service Bulletin (SB)
ehiers on DSK5VPTVN1PROD with RULES
material at the FAA, call 425–227–1221. MSB1078–200 (hereafter referred to as ‘‘the
Transportation, Docket Operations, M–
(5) You may view this service information SB’’ in this AD) to provide instructions for
that is incorporated by reference at the 30, West Building Ground Floor, Room inspections and corrective action.
National Archives and Records W12–140, 1200 New Jersey Avenue SE., For the reason described above, this AD
Administration (NARA). For information on Washington, DC 20590, between 9 a.m. requires repetitive inspections of the rear
the availability of this material at NARA, call and 5 p.m., Monday through Friday, horizontal stabilizer frame and modification
202–741–6030, or go to: http:// except Federal holidays. of the affected structure.
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Document Created: 2016-06-15 02:21:19
Document Modified: 2016-06-15 02:21:19
| 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 becomes effective July 20, 2016. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. | |
| FR Citation | 81 FR 38897 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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