80 FR 55229 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 178 (September 15, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 178 (September 15, 2015)
| Page Range | 55229-55232 | |
| FR Document | 2015-22924 |
[Federal Register Volume 80, Number 178 (Tuesday, September 15, 2015)] [Rules and Regulations] [Pages 55229-55232] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-22924] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-0926; Directorate Identifier 2014-NM-121-AD; Amendment 39-18263; AD 2015-18-05] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 97-07-14, for certain Airbus Model A320-111, -211, and -231 airplanes. AD 97-07-14 required modification of an area on the front spar of the wing center section by installing shims and new fasteners to reinforce pressure floor fittings. This new AD continues to require modifying the rib flange on the front spar of the wing center section by installing shims and new fasteners to reinforce pressure floor fittings; and requires repetitive high frequency eddy current inspections for cracking of the radius of the rib flanges and vertical stiffener at frame 36, a rototest inspection for cracking of the fastener holes of the rib flanges, repair if needed, and adding additional airplanes to the applicability. This AD was prompted by the need for repetitive inspections on airplanes on which the modification of the rib flange on the front spar of the wing center section has been done. We are issuing this AD to prevent fatigue cracking on the rib flange area of the front spar of the wing center section, which can reduce the structural integrity of fuselage frame 36 and the wing center section. DATES: This AD becomes effective October 20, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 20, 2015. The Director of the Federal Register approved the incorporation by reference [[Page 55230]] of a certain other publication listed in this AD as of May 12, 1997 (62 FR 16473, April 7, 1997). ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-0926; or in person at the 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. 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. 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- 0926. 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 to supersede AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997). AD 97-07-14 applied to certain Airbus Model A320-111, -211, and -231 airplanes. The NPRM published in the Federal Register on April 24, 2015 (80 FR 22943). Since we issued AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997), we have determined the need for repetitive inspections on airplanes on which Airbus Modification 20976 (modification of the rib flange on the front spar of the wing center section) was done in production, or was done using Airbus Service Bulletin A320-57-1013, dated April 12, 1989; or Airbus Service Bulletin A320-57-1013, Revision 1, dated September 29, 1992. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0053, dated March 7, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition on certain Airbus Model A320-211 and -231 airplanes. The MCAI states: During full scale fatigue tests on the Airbus A320 test specimen, cracks were found in the rib flange on the front spar side perpendicular to vertical posts at frame (FR) 36. It was determined that similar cracks could develop on certain in-service aeroplanes. This condition, if not detected and corrected, could affect the wing structural integrity. To reduce the risk of crack initiation, two modifications for aeroplanes in production and one modification for in-service aeroplanes were developed by Airbus: Prior to [manufacturer serial number] MSN 0085, the adaptation modification (Mod) 20976 was applied in production, consisting in installing shims under the fasteners linking the rib flange, the lower corner, the front spar and its vertical stiffener; from MSN 0085 onwards, the serial Mod 20908 was applied in production, consisting in installing reinforced lower surface rib flanges at front spar level. Airbus issued Service Bulletin (SB) A320-57-1013 for affected in-service aeroplanes, and [Directorate General for Civil Aviation] DGAC France issued AD [F-19]95-098-066 [dated May 24, 1995, which corresponds to FAA AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997), http://ad.easa.europa.eu/ad/F-1995-098-066] to require installation of shims under the fasteners linking the rib flange, the lower corner, the front spar and its vertical stiffener. Following a recent analysis, Airbus identified the need for repetitive [HFEC and rototest] inspections for aeroplanes on which Airbus SB A320-57-1013 or production Mod 20976 has been embodied. For the reason described above, this [EASA] AD retains the requirements of DGAC France AD [F-19]95-098-066, [dated May 24, 1995, which corresponds to FAA AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997), http://ad.easa.europa.eu/ad/F-1995-098-066], which is superseded, and requires repetitive [HFEC and rototest] inspections of the center wing lower ribs at FR 36 and, depending on findings, accomplishment of a repair. After EASA issued PAD 14-013, it was discovered that additional work [removal of shims and fasteners on the rib flange on the front spar side and doing an HFEC inspection for cracking of the radius of the rib flanges and a rototest inspection for cracking of the fastener holes during each inspection] to be included in Revision 01 of Airbus SB A320-57-1175, is required to accomplish the inspections. This Final [EASA] AD has been amended accordingly. Airplanes having MSNs 001, 009, and 015 were not included in the applicability of AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997). EASA AD 2014-0053, dated March 7, 2014, expanded the applicability to all airplanes having manufacturer serial numbers up to MSN 0084 inclusive. We included paragraph (h) of this AD to require the modification for the airplanes having MSNs 001, 009, and 015. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-0926-0002. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (80 FR 22943, April 24, 2015) or on the determination of the cost to the public. Conclusion We reviewed the available data 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 (80 FR 22943, April 24, 2015) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 22943, April 24, 2015). Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320-57-1175, Revision 01, including Appendix 01, dated May 28, 2014. The service information describes procedures for repetitive high frequency eddy current inspections for cracking of the radius of the rib flanges and vertical stiffener at frame 36, a rototest inspection for cracking of the fastener holes of the rib flanges, and repair. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this AD. Explanation of ``RC'' Procedures and Tests in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for annotating which procedures and tests in the service information are required for compliance with an AD. Differentiating these procedures and tests from other tasks in the service information is expected to improve an owner's/operator's understanding of crucial AD requirements and help [[Page 55231]] provide consistent judgment in AD compliance. The procedures and tests identified as Required for Compliance (RC) in any service information have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. As specified in a NOTE under the Accomplishment Instructions of the specified service information, procedures and tests that are identified as RC in any service information must be done to comply with the AD. However, procedures and tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an alternative method of compliance (AMOC), provided the procedures and tests identified as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to procedures or tests identified as RC will require approval of an AMOC. Costs of Compliance We estimate that this AD affects 11 airplanes of U.S. registry. The actions required by AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997), and retained in this AD take about 13 work-hours per product, at an average labor rate of $85 per work-hour. Required parts cost about $576 per product. Based on these figures, the estimated cost of the actions that were required by AD 97-07-14 is $1,681 per product. We also estimate that it will take about 45 work-hours per product to comply with the new basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $1,600 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $59,675, or $5,425 per product. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this 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. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-0926; 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 Operations office (telephone 800-647- 5527) is in the ADDRESSES section. 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 removing Airworthiness Directive (AD) 97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997), and adding the following new AD: 2015-18-05 Airbus: Amendment 39-18263. Docket No. FAA-2015-0926; Directorate Identifier 2014-NM-121-AD. (a) Effective Date This AD becomes effective October 20, 2015. (b) Affected ADs This AD replaces AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997). (c) Applicability This AD applies to Airbus Model A320-211 and -231 airplanes, certificated in any category, all manufacturer serial numbers (MSN) up to MSN 0084 inclusive. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by the determination that repetitive inspections are needed on airplanes on which the modification of the rib flange on the front spar of the wing center section has been done. We are issuing this AD to prevent fatigue cracking on the rib flange area of the front spar of the wing center section, which can reduce the structural integrity of fuselage frame 36 and the wing center section. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Modification This paragraph restates the requirements of paragraph (a) of AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997). For airplanes with manufacturer serial numbers (MSN) 005 through 008 inclusive, MSNs 010 through 014 inclusive, and MSNs 016 through 042 inclusive: Prior to the accumulation of 16,000 total landings, or within 3 months after May 12, 1997 (the effective date of AD 97-07- 14), whichever occurs later, modify the rib flange on the front spar of the wing center section by installing shims and new fasteners to reinforce pressure floor fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1013, Revision 1, dated September 29, 1992. (h) New Requirement of This AD: Modification for Airplanes With MSNs 001, 009, and 015 Prior to the accumulation of 16,000 total landings since first flight, or within 30 days after the effective date of this AD, whichever occurs later, modify the rib flange on the front spar of the wing center section by installing shims and new fasteners to reinforce pressure floor fittings, in [[Page 55232]] accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1013, Revision 1, dated September 29, 1992. (i) New Requirement of This AD: Repetitive Inspections Within the applicable compliance times specified in paragraphs (i)(1) and (i)(2) of this AD, do a high frequency eddy current (HFEC) inspection for cracking of the radius of the rib flanges and vertical stiffener at frame 36, and do a rototest inspection for cracking of the fastener holes of the rib flanges and vertical stiffener, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1175, Revision 01, including Appendix 01, dated May 28, 2014. During each inspection, remove the shims and fasteners on the rib flange on the front spar side and do an HFEC inspection for cracking of the radius of the rib flanges and a rototest inspection for cracking of the fastener holes. If no cracking is found, oversize the holes of the rib flange and the holes of the shims, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1175, Revision 01, including Appendix 01, dated May 28, 2014. Repeat the inspections thereafter at intervals not to exceed 32,500 flight cycles or 65,000 flight hours, whichever occurs first. (1) For airplanes having Airbus Modification 20976 embodied: At the later of the times specified in paragraphs (i)(1)(i) or (i)(1)(ii) of this AD. (i) Before exceeding 47,800 flight cycles or 95,600 flight hours, whichever occurs first, since the airplane's first flight. (ii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD. (2) For airplanes on which the modification of the front spar of the wing center section was accomplished using Airbus Service Bulletin A320-57-1013, Revision 1, dated September 29, 1992: At the later of the times specified in paragraphs (i)(2)(i) or (i)(2)(ii) of this AD. (i) Before exceeding 10,700 flight cycles or 21,500 flight hours, whichever occurs first, after the modification of the rib flange on the front spar of the wing center section was done using Airbus Service Bulletin A320-57-1013, Revision 1, dated September 29, 1992. (ii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD. (j) Repair If, during any inspection required by paragraph (i) of this AD, any cracking is found, before further flight, repair 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) Credit for Previous Actions This paragraph restates the requirements of Note 2 of paragraph (g) of AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997): This paragraph provides credit for the modification of the rib flange required by paragraph (g) of this AD, if those actions were performed before May 12, 1997 (the effective date of AD 97-07-14), using Airbus Service Bulletin A320-57-1013, dated April 12, 1989, which is not incorporated by reference in this AD. (l) 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. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, 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 EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (j) of this AD, if the service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures and tests that are not identified as RC are recommended. Those procedures and tests that are not identified 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 procedures and tests identified as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0053, dated March 7, 2014, 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-2015-0926. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (n)(5) and (n)(6) of this AD. (n) 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. (3) The following service information was approved for IBR on October 20, 2015. (i) Airbus Service Bulletin A320-57-1175, Revision 01, including Appendix 01, dated May 28, 2014. (ii) Reserved. (4) The following service information was approved for IBR on May 12, 1997 (62 FR 16473, April 7, 1997). (i) Airbus Service Bulletin A320-57-1013, Revision 1, dated September 29, 1992. Note 1 to paragraph (n)(4)(i): Airbus Service Bulletin A320-57- 1013, Revision 1, dated September 29, 1992, contains the following list of effective pages: Pages 1 through 3 show revision level 1, dated September 29, 1992; pages 4 through 11 are from the original issue, dated April 12, 1989. (ii) Reserved. (5) 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. (6) 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. (7) 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 September 2, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-22924 Filed 9-14-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 178 / Tuesday, September 15, 2015 / Rules and Regulations 55229
the type-certification basis under Conclusion special condition 3, above, must not
§ 21.17(a)(2). This action affects only certain novel prevent continued safe flight and
or unusual design features on one model landing.
Novel or Unusual Design Features
series of airplane. It is not a rule of Issued in Renton, Washington, on
The Model GVII–G500 airplane will general applicability. September 1, 2015.
incorporate the following novel or Michael Kaszycki,
unusual design features: Large-bypass List of Subjects in 14 CFR Part 25
Acting Manager, Transport Airplane
engines capable of larger and more Aircraft, Aviation safety, Reporting Directorate, Aircraft Certification Service.
complex dynamic loads than were and recordkeeping requirements. [FR Doc. 2015–23100 Filed 9–14–15; 8:45 am]
envisioned when the 14 CFR 25.361(b) The authority citation for these BILLING CODE 4910–13–P
rule was developed in 1957, thereby special conditions is as follows:
requiring issuance of special conditions Authority: 49 U.S.C. 106(g), 40113, 44701,
to establish appropriate design 44702, 44704. DEPARTMENT OF TRANSPORTATION
standards for the Model GVII–G500
airplane. The Special Conditions Federal Aviation Administration
Accordingly, pursuant to the
Discussion 14 CFR Part 39
authority delegated to me by the
The limit engine torque load imposed Administrator, the following special [Docket No. FAA–2015–0926; Directorate
by sudden engine stoppage due to conditions are issued as part of the type Identifier 2014–NM–121–AD; Amendment
malfunction or structural failure (such certification basis for the Gulfstream 39–18263; AD 2015–18–05]
as a compressor jamming) has been a Aerospace Corporation Model GVII–
G500 airplane. RIN 2120–AA64
specific requirement for transport-
category airplanes since 1957. In the In lieu of § 25.361(b) the following
Airworthiness Directives; Airbus
past, the design torque loads associated special conditions apply:
1. For turbine engine installations, the Airplanes
with typical failure scenarios have been
estimated by the engine manufacturer engine mounts, pylons, and adjacent AGENCY: Federal Aviation
and were provided to the airframe supporting airframe structure must be Administration (FAA), Department of
manufacturer as limit loads. These limit designed to withstand 1g level flight Transportation (DOT).
loads were considered simple, pure- loads acting simultaneously with the ACTION: Final rule.
torque static loads. maximum limit torque loads imposed
by each of the following: SUMMARY: We are superseding
It is evident from service history that a. Sudden engine deceleration due to Airworthiness Directive (AD) 97–07–14,
the engine-failure events that tend to a malfunction that could result in a for certain Airbus Model A320–111,
cause the most severe loads are fan- temporary loss of power or thrust, and –211, and –231 airplanes. AD 97–07–14
blade failures, and these events occur b. The maximum acceleration of the required modification of an area on the
much less frequently than the typical engine. front spar of the wing center section by
‘‘limit’’ load condition. 2. For auxiliary power unit (APU) installing shims and new fasteners to
To maintain the level of safety installations, the power unit mounts reinforce pressure floor fittings. This
envisioned by § 25.361(b), more and adjacent supporting airframe new AD continues to require modifying
comprehensive criteria are required for structure must be designed to withstand the rib flange on the front spar of the
the new generation of high-bypass 1g level-flight loads acting wing center section by installing shims
engines. These special conditions simultaneously with the maximum limit and new fasteners to reinforce pressure
distinguish between the more common torque loads imposed by each of the floor fittings; and requires repetitive
engine-failure events and those rare following: high frequency eddy current inspections
events resulting from structural failures. a. Sudden APU deceleration due to for cracking of the radius of the rib
The more-common events are regarded malfunction or structural failure; and flanges and vertical stiffener at frame 36,
as static torque limit load conditions. b. The maximum acceleration of the
a rototest inspection for cracking of the
The more-severe events resulting from APU.
fastener holes of the rib flanges, repair
3. For engine supporting structure, an
extreme engine-failure conditions (such if needed, and adding additional
ultimate loading condition must be
as loss of a full fan blade at redline airplanes to the applicability. This AD
considered that combines 1g flight loads
speed) are regarded as full dynamic load was prompted by the need for repetitive
with the transient dynamic loads
conditions. These are considered inspections on airplanes on which the
resulting from:
ultimate loads, and include all transient a. The loss of any fan, compressor, or modification of the rib flange on the
loads associated with the event. An turbine blade; and separately, front spar of the wing center section has
additional safety factor is applied to the b. Where applicable to a specific been done. We are issuing this AD to
more-critical airframe supporting engine design, any other engine prevent fatigue cracking on the rib
structure. structural failure that results in higher flange area of the front spar of the wing
Applicability loads. center section, which can reduce the
4. The ultimate loads developed from structural integrity of fuselage frame 36
As discussed above, these special the conditions specified in special and the wing center section.
conditions are applicable to the Model conditions 3(a) and 3(b), above, are to be DATES: This AD becomes effective
mstockstill on DSK4VPTVN1PROD with RULES
GVII–G500 airplane. Should Gulfstream multiplied by a factor of 1.0 when October 20, 2015.
Aerospace apply at a later date for a applied to engine mounts and pylons, The Director of the Federal Register
change to the type certificate to include and multiplied by a factor of 1.25 when approved the incorporation by reference
another model incorporating the same applied to adjacent supporting airframe of a certain publication listed in this AD
novel or unusual design feature, the structure. as of October 20, 2015.
special conditions would apply to that 5. Any permanent deformation that The Director of the Federal Register
model as well. results from the conditions specified in approved the incorporation by reference
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of a certain other publication listed in Information, or ‘‘the MCAI’’), to correct manufacturer serial numbers up to MSN
this AD as of May 12, 1997 (62 FR an unsafe condition on certain Airbus 0084 inclusive. We included paragraph
16473, April 7, 1997). Model A320–211 and –231 airplanes. (h) of this AD to require the
ADDRESSES: You may examine the AD The MCAI states: modification for the airplanes having
docket on the Internet at http:// During full scale fatigue tests on the Airbus MSNs 001, 009, and 015. You may
www.regulations.gov/ A320 test specimen, cracks were found in the examine the MCAI in the AD docket on
#!docketDetail;D=FAA-2015-0926; or in rib flange on the front spar side the Internet at http://
person at the Docket Management perpendicular to vertical posts at frame (FR) www.regulations.gov/
Facility, U.S. Department of 36. It was determined that similar cracks #!documentDetail;D=FAA-2015-0926-
could develop on certain in-service 0002.
Transportation, Docket Operations, M–
aeroplanes.
30, West Building Ground Floor, Room This condition, if not detected and Comments
W12–140, 1200 New Jersey Avenue SE., corrected, could affect the wing structural
Washington, DC. We gave the public the opportunity to
integrity.
For service information identified in To reduce the risk of crack initiation, two participate in developing this AD. We
this AD, contact Airbus, Airworthiness modifications for aeroplanes in production received no comments on the NPRM (80
Office—EIAS, 1 Rond Point Maurice and one modification for in-service FR 22943, April 24, 2015) or on the
Bellonte, 31707 Blagnac Cedex, France; aeroplanes were developed by Airbus: Prior determination of the cost to the public.
telephone +33 5 61 93 36 96; fax +33 5 to [manufacturer serial number] MSN 0085,
the adaptation modification (Mod) 20976 was Conclusion
61 93 44 51; email account.airworth- applied in production, consisting in
eas@airbus.com; Internet http:// We reviewed the available data and
installing shims under the fasteners linking determined that air safety and the
www.airbus.com. You may view this the rib flange, the lower corner, the front spar
referenced service information at the public interest require adopting this AD
and its vertical stiffener; from MSN 0085
FAA, Transport Airplane Directorate, onwards, the serial Mod 20908 was applied
as proposed except for minor editorial
1601 Lind Avenue SW., Renton, WA. in production, consisting in installing changes. We have determined that these
For information on the availability of reinforced lower surface rib flanges at front minor changes:
spar level. • Are consistent with the intent that
this material at the FAA, call 425–227–
Airbus issued Service Bulletin (SB) A320– was proposed in the NPRM (80 FR
1221. It is also available on the Internet
57–1013 for affected in-service aeroplanes, 22943, April 24, 2015) for correcting the
at http://www.regulations.gov by and [Directorate General for Civil Aviation] unsafe condition; and
searching for and locating Docket No. DGAC France issued AD [F–19]95–098–066 • Do not add any additional burden
FAA–2015–0926. [dated May 24, 1995, which corresponds to upon the public than was already
FOR FURTHER INFORMATION CONTACT: FAA AD 97–07–14, Amendment 39–9988 (62 proposed in the NPRM (80 FR 22943,
Sanjay Ralhan, Aerospace Engineer, FR 16473, April 7, 1997), http://
April 24, 2015).
International Branch, ANM–116, ad.easa.europa.eu/ad/F-1995-098-066] to
Transport Airplane Directorate, FAA, require installation of shims under the Related Service Information Under 1
fasteners linking the rib flange, the lower CFR Part 51
1601 Lind Avenue SW., Renton, WA corner, the front spar and its vertical
98057–3356; telephone 425–227–1405; stiffener. Airbus has issued Service Bulletin
fax 425–227–1149. Following a recent analysis, Airbus A320–57–1175, Revision 01, including
SUPPLEMENTARY INFORMATION: identified the need for repetitive [HFEC and Appendix 01, dated May 28, 2014. The
rototest] inspections for aeroplanes on which service information describes
Discussion Airbus SB A320–57–1013 or production Mod procedures for repetitive high frequency
We issued a notice of proposed 20976 has been embodied. eddy current inspections for cracking of
rulemaking (NPRM) to amend 14 CFR For the reason described above, this the radius of the rib flanges and vertical
[EASA] AD retains the requirements of DGAC
part 39 to supersede AD 97–07–14, stiffener at frame 36, a rototest
France AD [F–19]95–098–066, [dated May
Amendment 39–9988 (62 FR 16473, 24, 1995, which corresponds to FAA AD 97– inspection for cracking of the fastener
April 7, 1997). AD 97–07–14 applied to 07–14, Amendment 39–9988 (62 FR 16473, holes of the rib flanges, and repair. This
certain Airbus Model A320–111, –211, April 7, 1997), http://ad.easa.europa.eu/ad/ service information is reasonably
and –231 airplanes. The NPRM F-1995-098-066], which is superseded, and available because the interested parties
published in the Federal Register on requires repetitive [HFEC and rototest] have access to it through their normal
April 24, 2015 (80 FR 22943). inspections of the center wing lower ribs at course of business or by the means
Since we issued AD 97–07–14, FR 36 and, depending on findings, identified in the ADDRESSES section of
Amendment 39–9988 (62 FR 16473, accomplishment of a repair. this AD.
April 7, 1997), we have determined the After EASA issued PAD 14–013, it was
discovered that additional work [removal of Explanation of ‘‘RC’’ Procedures and
need for repetitive inspections on shims and fasteners on the rib flange on the
airplanes on which Airbus Modification Tests in Service Information
front spar side and doing an HFEC inspection
20976 (modification of the rib flange on for cracking of the radius of the rib flanges The FAA worked in conjunction with
the front spar of the wing center section) and a rototest inspection for cracking of the industry, under the Airworthiness
was done in production, or was done fastener holes during each inspection] to be Directive Implementation Aviation
using Airbus Service Bulletin A320–57– included in Revision 01 of Airbus SB A320– Rulemaking Committee (ARC), to
1013, dated April 12, 1989; or Airbus 57–1175, is required to accomplish the enhance the AD system. One
Service Bulletin A320–57–1013, inspections. This Final [EASA] AD has been enhancement was a new process for
Revision 1, dated September 29, 1992. amended accordingly. annotating which procedures and tests
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The European Aviation Safety Agency Airplanes having MSNs 001, 009, and in the service information are required
(EASA), which is the Technical Agent 015 were not included in the for compliance with an AD.
for the Member States of the European applicability of AD 97–07–14, Differentiating these procedures and
Union, has issued EASA Airworthiness Amendment 39–9988 (62 FR 16473, tests from other tasks in the service
Directive 2014–0053, dated March 7, April 7, 1997). EASA AD 2014–0053, information is expected to improve an
2014 (referred to after this as the dated March 7, 2014, expanded the owner’s/operator’s understanding of
Mandatory Continuing Airworthiness applicability to all airplanes having crucial AD requirements and help
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![Federal Register / Vol. 80, No. 178 / Tuesday, September 15, 2015 / Rules and Regulations 55231
provide consistent judgment in AD for practices, methods, and procedures § 39.13 [Amended]
compliance. The procedures and tests the Administrator finds necessary for ■ 2. The FAA amends § 39.13 by
identified as Required for Compliance safety in air commerce. This regulation removing Airworthiness Directive (AD)
(RC) in any service information have a is within the scope of that authority 97–07–14, Amendment 39–9988 (62 FR
direct effect on detecting, preventing, because it addresses an unsafe condition 16473, April 7, 1997), and adding the
resolving, or eliminating an identified that is likely to exist or develop on following new AD:
unsafe condition. products identified in this rulemaking
As specified in a NOTE under the 2015–18–05 Airbus: Amendment 39–18263.
action. Docket No. FAA–2015–0926; Directorate
Accomplishment Instructions of the Identifier 2014–NM–121–AD.
specified service information, Regulatory Findings
procedures and tests that are identified (a) Effective Date
We determined that this AD will not
as RC in any service information must have federalism implications under This AD becomes effective October 20,
be done to comply with the AD. Executive Order 13132. This AD will 2015.
However, procedures and tests that are not have a substantial direct effect on (b) Affected ADs
not identified as RC are recommended. the States, on the relationship between This AD replaces AD 97–07–14,
Those procedures and tests that are not the national government and the States, Amendment 39–9988 (62 FR 16473, April 7,
identified as RC may be deviated from or on the distribution of power and 1997).
using accepted methods in accordance responsibilities among the various
with the operator’s maintenance or (c) Applicability
levels of government.
inspection program without obtaining This AD applies to Airbus Model A320–
For the reasons discussed above, I 211 and -231 airplanes, certificated in any
approval of an alternative method of certify that this AD:
compliance (AMOC), provided the category, all manufacturer serial numbers
procedures and tests identified as RC 1. Is not a ‘‘significant regulatory (MSN) up to MSN 0084 inclusive.
can be done and the airplane can be put action’’ under Executive Order 12866; (d) Subject
back in a serviceable condition. Any 2. Is not a ‘‘significant rule’’ under the Air Transport Association (ATA) of
substitutions or changes to procedures DOT Regulatory Policies and Procedures America Code 57, Wings.
or tests identified as RC will require (44 FR 11034, February 26, 1979);
(e) Reason
approval of an AMOC. 3. Will not affect intrastate aviation in
Alaska; and This AD was prompted by the
Costs of Compliance determination that repetitive inspections are
4. Will not have a significant needed on airplanes on which the
We estimate that this AD affects 11 economic impact, positive or negative, modification of the rib flange on the front
airplanes of U.S. registry. on a substantial number of small entities spar of the wing center section has been
The actions required by AD 97–07–14, under the criteria of the Regulatory done. We are issuing this AD to prevent
Amendment 39–9988 (62 FR 16473, Flexibility Act. fatigue cracking on the rib flange area of the
April 7, 1997), and retained in this AD front spar of the wing center section, which
take about 13 work-hours per product, Examining the AD Docket can reduce the structural integrity of fuselage
at an average labor rate of $85 per work- frame 36 and the wing center section.
You may examine the AD docket on
hour. Required parts cost about $576 per the Internet at http:// (f) Compliance
product. Based on these figures, the www.regulations.gov/ Comply with this AD within the
estimated cost of the actions that were #!docketDetail;D=FAA-2015-0926; or in compliance times specified, unless already
required by AD 97–07–14 is $1,681 per person at the Docket Management done.
product. Facility between 9 a.m. and 5 p.m.,
We also estimate that it will take (g) Retained Modification
Monday through Friday, except Federal This paragraph restates the requirements of
about 45 work-hours per product to
holidays. The AD docket contains this paragraph (a) of AD 97–07–14, Amendment
comply with the new basic
AD, the regulatory evaluation, any 39–9988 (62 FR 16473, April 7, 1997). For
requirements of this AD. The average
comments received, and other airplanes with manufacturer serial numbers
labor rate is $85 per work-hour. (MSN) 005 through 008 inclusive, MSNs 010
information. The street address for the
Required parts will cost about $1,600 through 014 inclusive, and MSNs 016
Docket Operations office (telephone
per product. Based on these figures, we through 042 inclusive: Prior to the
800–647–5527) is in the ADDRESSES
estimate the cost of this AD on U.S. accumulation of 16,000 total landings, or
section.
operators to be $59,675, or $5,425 per within 3 months after May 12, 1997 (the
product. List of Subjects in 14 CFR Part 39 effective date of AD 97–07–14), whichever
occurs later, modify the rib flange on the
Authority for This Rulemaking Air transportation, Aircraft, Aviation front spar of the wing center section by
Title 49 of the United States Code safety, Incorporation by reference, installing shims and new fasteners to
specifies the FAA’s authority to issue Safety. reinforce pressure floor fittings, in
accordance with the Accomplishment
rules on aviation safety. Subtitle I, Adoption of the Amendment Instructions of Airbus Service Bulletin A320–
section 106, describes the authority of 57–1013, Revision 1, dated September 29,
the FAA Administrator. ‘‘Subtitle VII: Accordingly, under the authority 1992.
Aviation Programs,’’ describes in more delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as (h) New Requirement of This AD:
detail the scope of the Agency’s
follows: Modification for Airplanes With MSNs 001,
authority.
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009, and 015
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII, PART 39—AIRWORTHINESS Prior to the accumulation of 16,000 total
DIRECTIVES landings since first flight, or within 30 days
Part A, Subpart III, Section 44701: after the effective date of this AD, whichever
General requirements.’’ Under that occurs later, modify the rib flange on the
section, Congress charges the FAA with ■ 1. The authority citation for part 39
front spar of the wing center section by
promoting safe flight of civil aircraft in continues to read as follows: installing shims and new fasteners to
air commerce by prescribing regulations Authority: 49 U.S.C. 106(g), 40113, 44701. reinforce pressure floor fittings, in
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![55232 Federal Register / Vol. 80, No. 178 / Tuesday, September 15, 2015 / Rules and Regulations
accordance with the Accomplishment performed before May 12, 1997 (the effective (n) Material Incorporated by Reference
Instructions of Airbus Service Bulletin A320– date of AD 97–07–14), using Airbus Service (1) The Director of the Federal Register
57–1013, Revision 1, dated September 29, Bulletin A320–57–1013, dated April 12, approved the incorporation by reference
1992. 1989, which is not incorporated by reference (IBR) of the service information listed in this
(i) New Requirement of This AD: Repetitive in this AD. paragraph under 5 U.S.C. 552(a) and 1 CFR
Inspections (l) Other FAA AD Provisions part 51.
(2) You must use this service information
Within the applicable compliance times The following provisions also apply to this as applicable to do the actions required by
specified in paragraphs (i)(1) and (i)(2) of this AD: this AD, unless this AD specifies otherwise.
AD, do a high frequency eddy current (HFEC) (1) Alternative Methods of Compliance
inspection for cracking of the radius of the (3) The following service information was
(AMOCs): The Manager, International approved for IBR on October 20, 2015.
rib flanges and vertical stiffener at frame 36, Branch, ANM–116, Transport Airplane
and do a rototest inspection for cracking of (i) Airbus Service Bulletin A320–57–1175,
Directorate, FAA, has the authority to Revision 01, including Appendix 01, dated
the fastener holes of the rib flanges and
approve AMOCs for this AD, if requested May 28, 2014.
vertical stiffener, in accordance with the
using the procedures found in 14 CFR 39.19. (ii) Reserved.
Accomplishment Instructions of Airbus
In accordance with 14 CFR 39.19, send your (4) The following service information was
Service Bulletin A320–57–1175, Revision 01,
including Appendix 01, dated May 28, 2014. request to your principal inspector or local approved for IBR on May 12, 1997 (62 FR
During each inspection, remove the shims Flight Standards District Office, as 16473, April 7, 1997).
and fasteners on the rib flange on the front appropriate. If sending information directly (i) Airbus Service Bulletin A320–57–1013,
spar side and do an HFEC inspection for to the International Branch, send it to ATTN: Revision 1, dated September 29, 1992.
cracking of the radius of the rib flanges and Sanjay Ralhan, Aerospace Engineer, Note 1 to paragraph (n)(4)(i): Airbus
a rototest inspection for cracking of the International Branch, ANM–116, Transport Service Bulletin A320–57–1013, Revision 1,
fastener holes. If no cracking is found, Airplane Directorate, FAA, 1601 Lind dated September 29, 1992, contains the
oversize the holes of the rib flange and the Avenue SW., Renton, WA 98057–3356; following list of effective pages: Pages 1
holes of the shims, in accordance with the telephone 425–227–1405; fax 425–227–1149. through 3 show revision level 1, dated
Accomplishment Instructions of Airbus Information may be emailed to: 9-ANM-116- September 29, 1992; pages 4 through 11 are
Service Bulletin A320–57–1175, Revision 01, AMOC-REQUESTS@faa.gov. Before using from the original issue, dated April 12, 1989.
including Appendix 01, dated May 28, 2014. any approved AMOC, notify your appropriate (ii) Reserved.
Repeat the inspections thereafter at intervals principal inspector, or lacking a principal (5) For service information identified in
not to exceed 32,500 flight cycles or 65,000 inspector, the manager of the local flight this AD, contact Airbus, Airworthiness
flight hours, whichever occurs first. standards district office/certificate holding Office—EIAS, 1 Rond Point Maurice
(1) For airplanes having Airbus district office. The AMOC approval letter Bellonte, 31707 Blagnac Cedex, France;
Modification 20976 embodied: At the later of must specifically reference this AD. telephone +33 5 61 93 36 96; fax +33 5 61
the times specified in paragraphs (i)(1)(i) or (2) Contacting the Manufacturer: As of the 93 44 51; email account.airworth-eas@
(i)(1)(ii) of this AD. effective date of this AD, for any requirement airbus.com; Internet http://www.airbus.com.
(i) Before exceeding 47,800 flight cycles or in this AD to obtain corrective actions from (6) You may view this service information
95,600 flight hours, whichever occurs first, a manufacturer, the action must be at the FAA, Transport Airplane Directorate,
since the airplane’s first flight. accomplished using a method approved by 1601 Lind Avenue SW., Renton, WA. For
(ii) Within 850 flight cycles or 1,700 flight the Manager, International Branch, ANM– information on the availability of this
hours, whichever occurs first, after the 116, Transport Airplane Directorate, FAA; or material at the FAA, call 425–227–1221.
effective date of this AD. EASA; or Airbus’s EASA DOA. If approved (7) You may view this service information
(2) For airplanes on which the by the DOA, the approval must include the that is incorporated by reference at the
modification of the front spar of the wing DOA-authorized signature. National Archives and Records
center section was accomplished using (3) Required for Compliance (RC): Except Administration (NARA). For information on
Airbus Service Bulletin A320–57–1013, as required by paragraph (j) of this AD, if the the availability of this material at NARA, call
Revision 1, dated September 29, 1992: At the service information contains procedures or 202–741–6030, or go to: http://
later of the times specified in paragraphs tests that are identified as RC, those www.archives.gov/federal-register/cfr/ibr-
(i)(2)(i) or (i)(2)(ii) of this AD. procedures and tests must be done to comply locations.html.
(i) Before exceeding 10,700 flight cycles or with this AD; any procedures and tests that
21,500 flight hours, whichever occurs first, are not identified as RC are recommended. Issued in Renton, Washington, on
after the modification of the rib flange on the Those procedures and tests that are not September 2, 2015.
front spar of the wing center section was identified as RC may be deviated from using Jeffrey E. Duven,
done using Airbus Service Bulletin A320– accepted methods in accordance with the Manager, Transport Airplane Directorate,
57–1013, Revision 1, dated September 29, operator’s maintenance or inspection Aircraft Certification Service.
1992. program without obtaining approval of an
(ii) Within 850 flight cycles or 1,700 flight [FR Doc. 2015–22924 Filed 9–14–15; 8:45 am]
AMOC, provided the procedures and tests
hours, whichever occurs first, after the BILLING CODE 4910–13–P
identified as RC can be done and the airplane
effective date of this AD.
can be put back in a serviceable condition.
(j) Repair Any substitutions or changes to procedures
or tests identified as RC require approval of DEPARTMENT OF TRANSPORTATION
If, during any inspection required by
paragraph (i) of this AD, any cracking is an AMOC.
Federal Aviation Administration
found, before further flight, repair using a (m) Related Information
method approved by the Manager,
International Branch, ANM–116, Transport (1) Refer to Mandatory Continuing 14 CFR Part 39
Airplane Directorate, FAA; or the European Airworthiness Information (MCAI) EASA
[Docket No. FAA–2014–0363; Directorate
Aviation Safety Agency (EASA); or Airbus’s Airworthiness Directive 2014–0053, dated
Identifier 2014–NE–08–AD; Amendment 39–
EASA Design Organization Approval (DOA). March 7, 2014, for related information. This
18252; AD 2015–17–19]
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MCAI may be found in the AD docket on the
(k) Credit for Previous Actions Internet at http://www.regulations.gov by RIN 2120–AA64
This paragraph restates the requirements of searching for and locating Docket No. FAA–
Note 2 of paragraph (g) of AD 97–07–14, 2015–0926. Airworthiness Directives; Rolls-Royce
Amendment 39–9988 (62 FR 16473, April 7, (2) Service information identified in this plc Turbofan Engines
1997): This paragraph provides credit for the AD that is not incorporated by reference is
modification of the rib flange required by available at the addresses specified in AGENCY:Federal Aviation
paragraph (g) of this AD, if those actions were paragraphs (n)(5) and (n)(6) of this AD. Administration (FAA), DOT.
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Document Created: 2015-12-15 10:09:20
Document Modified: 2015-12-15 10:09:20
| 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 October 20, 2015. | |
| 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 | 80 FR 55229 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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