82 FR 30958 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 127 (July 5, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 127 (July 5, 2017)
| Page Range | 30958-30961 | |
| FR Document | 2017-13763 |
[Federal Register Volume 82, Number 127 (Wednesday, July 5, 2017)] [Rules and Regulations] [Pages 30958-30961] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-13763] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-0461; Directorate Identifier 2014-NM-159-AD; Amendment 39-18937; AD 2017-13-07] 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 A319, A320, and A321 series airplanes. This AD was prompted by a report that a main landing gear (MLG) door could not be closed due to rupture of the actuator fitting. This AD requires repetitive inspections for cracking of the MLG door actuator fitting and its components, and corrective actions if necessary. This AD also requires eventual replacement of all affected MLG door actuator fittings with new monoblock fittings, which would terminate the repetitive inspections. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective August 9, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 9, 2017. 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-2016- 0461. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 0461; 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 supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A319, A320, and A321 series airplanes. The SNPRM published in the Federal Register on April 7, 2017 (82 FR 16948) (``the SNPRM''). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on January 28, 2016 (81 FR 4901) (``the NPRM''). The NPRM proposed to require repetitive inspections for cracking of the MLG door actuator fitting and its components, and corrective actions if necessary. The NPRM also proposed to require eventual replacement of all affected MLG door actuator fittings with new monoblock fittings, which would terminate the repetitive inspections. The NPRM was prompted by a report that an MLG door could not be closed due to rupture of the actuator fitting. The SNPRM proposed to revise the NPRM by reducing the compliance time for replacing the MLG actuator fitting and removing an inspection requirement for certain airplanes. We are issuing this AD to prevent rupture of the door actuator fittings, which could result in detachment of an MLG door and subsequent exterior damage and consequent 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 2016-0182, dated September 13, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A319, A320, and A321 series airplanes. The MCAI states: On one A320 aeroplane, it was reported that one of the main landing gear (MLG) doors could not be closed. Investigations revealed the rupture of the actuator fitting at the actuator attachment area on the door side. The MLG door is attached to the aeroplane by 2 (two) hinge fittings. This condition, if not corrected, could, under certain circumstances, lead to detachment of a MLG door from the aeroplane, possibly resulting in damage to the aeroplane, and/or injury to persons on the ground. Prompted by these findings, [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France issued * * * [an AD] * * *, to require a MLG door actuator fitting inspection for cracks and to check the grain direction on a batch of aeroplanes. Subsequently, DGAC France issued * * * [an AD], retaining the requirements of DGAC France AD * * *, which was superseded, to require an inspection of the lower part of the MLG door actuator fitting. After that [DGAC] AD was issued, additional investigations revealed that damage could also appear on the nerve area [of the forward monoblock fitting], in the upper part of the MLG door actuator fitting in the area of the hinge. Consequently, DGAC France issued F-2003-434, dated December 10, 2003 [http://ad.easa.europa.eu/ad/F-2003-454] (EASA approval 2003- 1436), retaining the requirements of [a] DGAC France AD * * *, which was superseded, to require additional repetitive inspections. That [DGAC] AD also included an optional terminating action, by replacing the MLG door actuator fittings in accordance with the instructions of Airbus Service Bulletin (SB) A320-52-1073. After DGAC France AD F-2003-434 was issued, in the framework of the extended service goal campaign, it was decided to make replacement of the MLG door actuator fittings a required modification. Consequently, EASA issued AD 2014-0166 * * *, retaining the requirements of DGAC France AD F-2003-434, which was superseded, and requiring replacement of the MLG door actuator fittings with new monoblock fittings, which constitutes terminating action for the repetitive inspections. After EASA AD 2014-0166 [corresponding to the NPRM] was issued, errors were identified in the compliance time definitions. [[Page 30959]] Replacement of the MLG door actuator fittings was required ``before exceeding 48,000 flight cycles (FC) or 96,000 flight hours (FH), whichever occurs later since aeroplane first flight'', which should have been ``whichever occurs first''. Furthermore, since the MLG door is an interchangeable part, the compliance time must be defined as FC/FH accumulated by the MLG door. Furthermore, it was discovered that one of the required inspection[s] is applicable only to a batch of MLG door fittings. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2014-0166, which is superseded, but requires accomplishment of the terminating action within more stringent compliance times, and reduce[s] the applicability of one of the required inspection[s]. 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-2016- 0461. Comments We gave the public the opportunity to participate in developing this AD. We considered the comments received. United Airlines and commenter Lisa Stamps supported the SNPRM. Clarification of Provisions for Excluded Airplanes In paragraph (l)(1) of the proposed AD (in the SNPRM), we inadvertently omitted wording related to the prohibition on installing certain MLG door actuator fittings on modified airplanes, which is identified in step 10 of the EASA AD. We have added that provision to paragraph (l)(1) of this AD. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the change described previously, except for minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the SNPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the SNPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information: Airbus Service Bulletin A320-52-1073, Revision 04, dated August 10, 1999. Airbus Service Bulletin A320-52-1073, Revision 05, dated September 28, 2006. This service information describes procedures for replacement of MLG door actuator fittings with new monoblock fittings. These documents are distinct due to editorial revisions. Airbus has also issued the following service information: Airbus Service Bulletin A320-52A1086, Revision 01, dated September 10, 1999. This service information describes procedures for high frequency eddy current (HFEC) inspections for cracking of the MLG door fittings, and low frequency eddy current (LFEC) inspections to determine grain direction of raw material of each actuator fitting. Airbus Service Bulletin A320-52-1096, Revision 02, dated July 12, 2006. This service information describes procedures for HFEC inspections of both hinge and nerve areas of the MLG doors for cracking. 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 71 airplanes of U.S. registry. We also estimate that it takes about 136 work-hours per product to comply with the requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $6,258 per product. Based on these figures, we estimate the cost for the actions required by this AD on U.S. operators to be $1,265,078, or $17,818 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. 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): 2017-13-07 Airbus: Amendment 39-18937; Docket No. FAA-2016-0461; Directorate Identifier 2014-NM-159-AD. (a) Effective Date This AD is effective August 9, 2017. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes, certificated in any category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, all manufacturer serial numbers. (1) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes. (2) Model A320-211, -212, -214, -231, -232, and -233 airplanes. (3) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Reason This AD was prompted by a report that a main landing gear (MLG) door could not be closed due to rupture of the actuator fitting. [[Page 30960]] Later reports indicated that the forward monoblock fitting of the MLG door actuator (referred to as the nerve area) could be damaged after rupture of the actuator fitting. We are issuing this AD to prevent rupture of the door actuator fittings, which could result in detachment of an MLG door and subsequent exterior damage and consequent reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections of MLG Door Actuator Fittings For airplanes equipped with MLG door actuator fittings having part number (P/N) D52880224000 or P/N D52880224001 that were installed before the first flight of the airplane on MLG doors identified in paragraphs (g)(1) and (g)(2) of this AD: Within 500 flight hours since the most recent high frequency eddy current (HFEC) inspection done as specified in Airbus Service Bulletin A320- 52A1086, Revision 01, dated September 10, 1999, or within 30 days after the effective date of this AD, whichever occurs later, perform an HFEC inspection for cracking of the MLG door fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52A1086, Revision 01, dated September 10, 1999. Repeat the inspection thereafter at intervals not to exceed 500 flight hours, except as provided by paragraphs (i), (j), and (k) of this AD. (1) Left-hand MLG doors with serial numbers (S/Ns) 1206 through 1237 inclusive, 1239 through 1247 inclusive, and 1249 through 1251 inclusive. (2) Right-hand MLG doors with S/Ns 1208 through 1239 inclusive, 1241 through 1249 inclusive, and 1251. (h) Repetitive Inspections of MLG Hinge and Nerve Areas For airplanes equipped with MLG door actuator fittings having P/ N D52880224000, P/N D52880224001, P/N D52880235000, or P/N D52880235001 that were installed before the first flight of the airplane on MLG doors identified in paragraphs (h)(1) and (h)(2) of this AD: Within 400 flight cycles after the effective date of this AD, or before the accumulation of 9,000 total flight cycles since first flight of the airplane, whichever occurs later, perform an HFEC inspection of both hinge and nerve areas of the MLG doors for cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1096, Revision 02, dated July 12, 2006. Repeat the inspection thereafter at intervals not to exceed 800 flight cycles, except as provided by paragraphs (i)(1), (j), and (k) of this AD. (1) Left-hand MLG doors with S/Ns 1206 through 1510 inclusive, 1548, 1564, and 2000 through 2065 inclusive. (2) Right-hand MLG doors with S/Ns 1208 through 1519 inclusive, 1551, and 2000 through 2065 inclusive. (i) Inspections/Corrective Actions (1) If any crack is found during any inspection required by paragraph (g) or (h) of this AD: Before further flight, replace the affected MLG door actuator fittings with new monoblock fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1073, Revision 05, dated September 28, 2006. Accomplishing this replacement terminates the repetitive inspections required by paragraphs (g) and (h) of this AD. (2) If, during any HFEC inspection required by paragraph (g) of this AD, no crack is found: Before further flight, perform a low frequency eddy current (LFEC) inspection to determine the grain direction of the raw material of each MLG actuator fitting, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52A1086, Revision 01, dated September 10, 1999. (i) If the grain direction of the raw material is correct, the repetitive inspections required by paragraph (g) of this AD may be terminated. (ii) If the grain direction of the raw material is incorrect, repeat the HFEC inspection required by paragraph (g) of this AD at the time specified in paragraph (g) of this AD. Replacement of the MLG door actuator fittings with new monoblock fittings as specified in paragraph (i)(1) of this AD terminates the repetitive inspections required by paragraphs (g) and (i)(2)(ii) of this AD. (j) MLG Door Actuator Fitting Replacement For airplanes equipped with any MLG door actuator fitting having P/N D52880102000, P/N D52880102001, P/N D52880220000, P/N D52880220001, P/N D52880224000, P/N D52880224001, P/N D52880235000, or P/N D52880235001: At the later of the times specified in paragraphs (j)(1) and (j)(2) of this AD, replace the MLG door actuator fittings with new monoblock fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52- 1073, Revision 05, dated September 28, 2006. Accomplishing this replacement terminates the repetitive inspections required by paragraphs (g) and (h) of this AD. (1) Before the accumulation of 48,000 total flight cycles or 96,000 total flight hours on the MLG door, whichever occurs first. (2) Within 30 days after the effective date of this AD. (k) Optional Terminating Action Replacement of the MLG door actuator fittings with new monoblock fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1073, Revision 04, dated August 10, 1999; or Airbus Service Bulletin A320-52-1073, Revision 05, dated September 28, 2006; terminates the repetitive inspections required by paragraphs (g) and (h) of this AD. (l) Airplanes Excluded From Certain AD Requirements (1) For airplanes on which Airbus Modification 24903, or Airbus Modification 25372, or Airbus Modification 36979 has been embodied in production, no action is required by this AD, provided that no MLG door actuator fitting having any part number identified in paragraph (j) of this AD has been reinstalled on the airplane since first flight; except the requirements of paragraph (m) of this AD remain applicable to post-mod 24903, post-mod 25372 and post-mod 36979 airplanes. (2) Modification of an airplane by installing a version (P/N) of the MLG door actuator fitting approved after the effective date of this AD is acceptable for compliance with the requirements in paragraph (j) of this AD, provided the conditions specified in paragraphs (l)(2)(i) and (l)(2)(ii) are met. (i) The MLG door actuator fitting (P/N) must be 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). (ii) The modification must be accomplished in accordance with instructions approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; EASA; or Airbus's EASA DOA. (m) Parts Installation Prohibition As of the effective date of this AD, no person may install an MLG door actuator fitting having any part number identified in paragraph (j) of this AD on any airplane. (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 the person identified in paragraph (o)(2) of this AD. 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 2016-0182, dated September 13, 2016, 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-2016-0461. (2) For more information about this AD, 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. [[Page 30961]] (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 Service Bulletin A320-52-1073, Revision 04, dated August 10, 1999. (ii) Airbus Service Bulletin A320-52-1073, Revision 05, dated September 28, 2006. (iii) Airbus Service Bulletin A320-52A1086, Revision 01, dated September 10, 1999. (iv) Airbus Service Bulletin A320-52-1096, Revision 02, dated July 12, 2006. (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 June 19, 2017. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-13763 Filed 7-3-17; 8:45 am] BILLING CODE 4910-13-P
![30958 Federal Register / Vol. 82, No. 127 / Wednesday, July 5, 2017 / Rules and Regulations
District Avenue, Burlington, MA 01803. For information at the FAA, Transport AD to prevent rupture of the door
information on the availability of this Airplane Directorate, 1601 Lind Avenue actuator fittings, which could result in
material at the FAA, call 781–238–7125. SW., Renton, WA. For information on detachment of an MLG door and
(5) You may view this service information the availability of this material at the subsequent exterior damage and
at the National Archives and Records
Administration (NARA). For information on
FAA, call 425–227–1221. It is also consequent reduced structural integrity
the availability of this material at NARA, call available on the Internet at http:// of the airplane.
202–741–6030, or go to: http:// www.regulations.gov by searching for The European Aviation Safety Agency
www.archives.gov/federal-register/cfr/ibr- and locating Docket No. FAA–2016– (EASA), which is the Technical Agent
locations.html. 0461. for the Member States of the European
Issued in Burlington, Massachusetts, on Union, has issued EASA Airworthiness
Examining the AD Docket Directive 2016–0182, dated September
May 11, 2017.
Robert J. Ganley,
You may examine the AD docket on 13, 2016 (referred to after this as the
the Internet at http:// Mandatory Continuing Airworthiness
Acting Manager, Engine & Propeller
Directorate, Aircraft Certification Service.
www.regulations.gov by searching for Information, or ‘‘the MCAI’’), to correct
and locating Docket No. FAA–2016– an unsafe condition for all Airbus
[FR Doc. 2017–14050 Filed 7–3–17; 8:45 am]
0461; or in person at the Docket Model A319, A320, and A321 series
BILLING CODE 4910–13–P
Management Facility between 9 a.m. airplanes. The MCAI states:
and 5 p.m., Monday through Friday, On one A320 aeroplane, it was reported
DEPARTMENT OF TRANSPORTATION except Federal holidays. The AD docket that one of the main landing gear (MLG)
contains this AD, the regulatory doors could not be closed. Investigations
Federal Aviation Administration evaluation, any comments received, and revealed the rupture of the actuator fitting at
other information. The street address for the actuator attachment area on the door side.
the Docket Office (telephone 800–647– The MLG door is attached to the aeroplane
14 CFR Part 39 by 2 (two) hinge fittings.
5527) is Docket Management Facility,
[Docket No. FAA–2016–0461; Directorate This condition, if not corrected, could,
U.S. Department of Transportation, under certain circumstances, lead to
Identifier 2014–NM–159–AD; Amendment
Docket Operations, M–30, West detachment of a MLG door from the
39–18937; AD 2017–13–07]
Building Ground Floor, Room W12–140, aeroplane, possibly resulting in damage to
RIN 2120–AA64 1200 New Jersey Avenue SE., the aeroplane, and/or injury to persons on
Washington, DC 20590. the ground.
Airworthiness Directives; Airbus Prompted by these findings, [Direction
FOR FURTHER INFORMATION CONTACT:
Airplanes Générale de l’Aviation Civile] France issued
Sanjay Ralhan, Aerospace Engineer,
* * * [an AD] * * *, to require a MLG door
AGENCY: Federal Aviation International Branch, ANM–116, actuator fitting inspection for cracks and to
Administration (FAA), Department of Transport Airplane Directorate, FAA, check the grain direction on a batch of
Transportation (DOT). 1601 Lind Avenue SW., Renton, WA aeroplanes. Subsequently, DGAC France
ACTION: Final rule. 98057–3356; telephone 425–227–1405; issued * * * [an AD], retaining the
fax 425–227–1149. requirements of DGAC France AD * * *,
SUMMARY: We are adopting a new SUPPLEMENTARY INFORMATION:
which was superseded, to require an
airworthiness directive (AD) for all inspection of the lower part of the MLG door
Airbus Model A319, A320, and A321 Discussion actuator fitting.
series airplanes. This AD was prompted After that [DGAC] AD was issued,
We issued a supplemental notice of additional investigations revealed that
by a report that a main landing gear proposed rulemaking (SNPRM) to damage could also appear on the nerve area
(MLG) door could not be closed due to amend 14 CFR part 39 by adding an AD [of the forward monoblock fitting], in the
rupture of the actuator fitting. This AD that would apply to all Airbus Model upper part of the MLG door actuator fitting
requires repetitive inspections for A319, A320, and A321 series airplanes. in the area of the hinge.
cracking of the MLG door actuator The SNPRM published in the Federal Consequently, DGAC France issued F–
fitting and its components, and 2003–434, dated December 10, 2003 [http://
Register on April 7, 2017 (82 FR 16948)
corrective actions if necessary. This AD ad.easa.europa.eu/ad/F-2003-454] (EASA
(‘‘the SNPRM’’). We preceded the approval 2003–1436), retaining the
also requires eventual replacement of all SNPRM with a notice of proposed requirements of [a] DGAC France AD * * *,
affected MLG door actuator fittings with rulemaking (NPRM) that published in which was superseded, to require additional
new monoblock fittings, which would the Federal Register on January 28, repetitive inspections. That [DGAC] AD also
terminate the repetitive inspections. We 2016 (81 FR 4901) (‘‘the NPRM’’). The included an optional terminating action, by
are issuing this AD to address the unsafe NPRM proposed to require repetitive replacing the MLG door actuator fittings in
condition on these products. inspections for cracking of the MLG accordance with the instructions of Airbus
DATES: This AD is effective August 9, Service Bulletin (SB) A320–52–1073.
door actuator fitting and its
After DGAC France AD F–2003–434 was
2017. components, and corrective actions if issued, in the framework of the extended
The Director of the Federal Register necessary. The NPRM also proposed to service goal campaign, it was decided to
approved the incorporation by reference require eventual replacement of all make replacement of the MLG door actuator
of certain publications listed in this AD affected MLG door actuator fittings with fittings a required modification.
as of August 9, 2017. new monoblock fittings, which would Consequently, EASA issued AD 2014–0166
ADDRESSES: For service information terminate the repetitive inspections. The * * *, retaining the requirements of DGAC
identified in this final rule, contact NPRM was prompted by a report that an France AD F–2003–434, which was
sradovich on DSK3GMQ082PROD with RULES
Airbus, Airworthiness Office—EIAS, 1 MLG door could not be closed due to superseded, and requiring replacement of the
MLG door actuator fittings with new
Rond Point Maurice Bellonte, 31707 rupture of the actuator fitting. The
monoblock fittings, which constitutes
Blagnac Cedex, France; telephone +33 5 SNPRM proposed to revise the NPRM terminating action for the repetitive
61 93 36 96; fax +33 5 61 93 44 51; email by reducing the compliance time for inspections.
account.airworth-eas@airbus.com; replacing the MLG actuator fitting and After EASA AD 2014–0166 [corresponding
Internet http://www.airbus.com. You removing an inspection requirement for to the NPRM] was issued, errors were
may view this referenced service certain airplanes. We are issuing this identified in the compliance time definitions.
VerDate Sep<11>2014 16:11 Jul 03, 2017 Jkt 241001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\05JYR1.SGM 05JYR1](https://thefederalregister.org/doc/82_FR_31085/page/1.svg)
![Federal Register / Vol. 82, No. 127 / Wednesday, July 5, 2017 / Rules and Regulations 30959
Replacement of the MLG door actuator door actuator fittings with new the States, on the relationship between
fittings was required ‘‘before exceeding monoblock fittings. These documents the national government and the States,
48,000 flight cycles (FC) or 96,000 flight are distinct due to editorial revisions. or on the distribution of power and
hours (FH), whichever occurs later since Airbus has also issued the following responsibilities among the various
aeroplane first flight’’, which should have
been ‘‘whichever occurs first’’. Furthermore,
service information: levels of government.
since the MLG door is an interchangeable • Airbus Service Bulletin A320– For the reasons discussed above, I
part, the compliance time must be defined as 52A1086, Revision 01, dated September certify that this AD:
FC/FH accumulated by the MLG door. 10, 1999. This service information 1. Is not a ‘‘significant regulatory
Furthermore, it was discovered that one of describes procedures for high frequency action’’ under Executive Order 12866;
the required inspection[s] is applicable only eddy current (HFEC) inspections for 2. Is not a ‘‘significant rule’’ under the
to a batch of MLG door fittings. cracking of the MLG door fittings, and DOT Regulatory Policies and Procedures
For the reason described above, this low frequency eddy current (LFEC) (44 FR 11034, February 26, 1979);
[EASA] AD retains the requirements of EASA inspections to determine grain direction 3. Will not affect intrastate aviation in
AD 2014–0166, which is superseded, but
of raw material of each actuator fitting. Alaska; and
requires accomplishment of the terminating
action within more stringent compliance • Airbus Service Bulletin A320–52– 4. Will not have a significant
times, and reduce[s] the applicability of one 1096, Revision 02, dated July 12, 2006. economic impact, positive or negative,
of the required inspection[s]. This service information describes on a substantial number of small entities
procedures for HFEC inspections of both under the criteria of the Regulatory
You may examine the MCAI in the Flexibility Act.
hinge and nerve areas of the MLG doors
AD docket on the Internet at http://
for cracking. List of Subjects in 14 CFR Part 39
www.regulations.gov by searching for This service information is reasonably
and locating Docket No. FAA–2016– available because the interested parties Air transportation, Aircraft, Aviation
0461. have access to it through their normal safety, Incorporation by reference,
Comments course of business or by the means Safety.
We gave the public the opportunity to identified in the ADDRESSES section. Adoption of the Amendment
participate in developing this AD. We Costs of Compliance Accordingly, under the authority
considered the comments received. delegated to me by the Administrator,
We estimate that this AD affects 71
United Airlines and commenter Lisa the FAA amends 14 CFR part 39 as
airplanes of U.S. registry.
Stamps supported the SNPRM. We also estimate that it takes about follows:
Clarification of Provisions for Excluded 136 work-hours per product to comply
Airplanes with the requirements of this AD. The PART 39—AIRWORTHINESS
average labor rate is $85 per work-hour. DIRECTIVES
In paragraph (l)(1) of the proposed AD
(in the SNPRM), we inadvertently Required parts will cost about $6,258
■ 1. The authority citation for part 39
omitted wording related to the per product. Based on these figures, we
continues to read as follows:
prohibition on installing certain MLG estimate the cost for the actions required
by this AD on U.S. operators to be Authority: 49 U.S.C. 106(g), 40113, 44701.
door actuator fittings on modified
airplanes, which is identified in step 10 $1,265,078, or $17,818 per product. § 39.13 [Amended]
of the EASA AD. We have added that Authority for This Rulemaking ■ 2. The FAA amends § 39.13 by adding
provision to paragraph (l)(1) of this AD. Title 49 of the United States Code the following new airworthiness
Conclusion specifies the FAA’s authority to issue directive (AD):
We reviewed the relevant data, rules on aviation safety. Subtitle I, 2017–13–07 Airbus: Amendment 39–18937;
considered the comments received, and section 106, describes the authority of Docket No. FAA–2016–0461; Directorate
determined that air safety and the the FAA Administrator. ‘‘Subtitle VII: Identifier 2014–NM–159–AD.
public interest require adopting this AD Aviation Programs,’’ describes in more (a) Effective Date
with the change described previously, detail the scope of the Agency’s
authority. This AD is effective August 9, 2017.
except for minor editorial changes. We
have determined that these minor We are issuing this rulemaking under (b) Affected ADs
changes: the authority described in ‘‘Subtitle VII, None.
• Are consistent with the intent that Part A, Subpart III, Section 44701:
General requirements.’’ Under that (c) Applicability
was proposed in the SNPRM for
section, Congress charges the FAA with This AD applies to the Airbus airplanes,
correcting the unsafe condition; and certificated in any category, identified in
• Do not add any additional burden promoting safe flight of civil aircraft in
air commerce by prescribing regulations paragraphs (c)(1), (c)(2), and (c)(3) of this AD,
upon the public than was already all manufacturer serial numbers.
proposed in the SNPRM. for practices, methods, and procedures
(1) Model A319–111, –112, –113, –114,
the Administrator finds necessary for –115, –131, –132, and –133 airplanes.
Related Service Information Under 1 safety in air commerce. This regulation (2) Model A320–211, –212, –214, –231,
CFR Part 51 is within the scope of that authority –232, and –233 airplanes.
Airbus has issued the following because it addresses an unsafe condition (3) Model A321–111, –112, –131, –211,
service information: that is likely to exist or develop on –212, –213, –231, and –232 airplanes.
• Airbus Service Bulletin A320–52– products identified in this rulemaking (d) Subject
sradovich on DSK3GMQ082PROD with RULES
1073, Revision 04, dated August 10, action.
Air Transport Association (ATA) of
1999.
• Airbus Service Bulletin A320–52– Regulatory Findings America Code 52, Doors.
1073, Revision 05, dated September 28, We determined that this AD will not (e) Reason
2006. have federalism implications under This AD was prompted by a report that a
This service information describes Executive Order 13132. This AD will main landing gear (MLG) door could not be
procedures for replacement of MLG not have a substantial direct effect on closed due to rupture of the actuator fitting.
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![Federal Register / Vol. 82, No. 127 / Wednesday, July 5, 2017 / Rules and Regulations 30961
(p) Material Incorporated by Reference locations of the frame web, and cracking at the station (STA) 344 system
(1) The Director of the Federal Register corrective action if necessary. We are penetration holes between stringer S–
approved the incorporation by reference issuing this AD to address the unsafe 22L and stringer S–24L. The NPRM
(IBR) of the service information listed in this condition on these products. proposed to require repetitive
paragraph under 5 U.S.C. 552(a) and 1 CFR DATES: This AD is effective August 9, inspections in certain locations of the
part 51. frame web, and corrective action if
(2) You must use this service information 2017.
as applicable to do the actions required by The Director of the Federal Register necessary. We are issuing this AD to
this AD, unless this AD specifies otherwise. approved the incorporation by reference detect and correct frame web cracking,
(i) Airbus Service Bulletin A320–52–1073, of a certain publication listed in this AD which could grow in size until frames
Revision 04, dated August 10, 1999. as of August 9, 2017. sever. Multiple adjacent severed frames,
(ii) Airbus Service Bulletin A320–52–1073, ADDRESSES: For service information or a severed frame near cracks in the
Revision 05, dated September 28, 2006. identified in this final rule, contact chem-milled fuselage skin, could result
(iii) Airbus Service Bulletin A320– in uncontrolled decompression of the
52A1086, Revision 01, dated September 10,
Boeing Commercial Airplanes,
Attention: Contractual & Data Services airplane.
1999.
(iv) Airbus Service Bulletin A320–52– (C&DS), 2600 Westminster Blvd., MC Comments
1096, Revision 02, dated July 12, 2006. 110–SK57, Seal Beach, CA 90740–5600;
(3) For service information identified in telephone 562–797–1717; Internet We gave the public the opportunity to
this AD, contact Airbus, Airworthiness https://www.myboeingfleet.com. You participate in developing this AD. The
Office—EIAS, 1 Rond Point Maurice may view this service information at the following presents the comments
Bellonte, 31707 Blagnac Cedex, France; FAA, Transport Airplane Directorate, received on the NPRM and the FAA’s
telephone +33 5 61 93 36 96; fax +33 5 61
1601 Lind Avenue SW., Renton, WA. response to each comment.
93 44 51; email account.airworth-eas@
airbus.com; Internet http://www.airbus.com. For information on the availability of
Request To Change Inspection and
(4) You may view this service information this material at the FAA, call 425–227–
Corrective Actions for Group 1
at the FAA, Transport Airplane Directorate, 1221. It is also available on the Internet
Airplanes
1601 Lind Avenue SW., Renton, WA. For at http://www.regulations.gov by
information on the availability of this searching for and locating Docket No. Boeing requested that we change the
material at the FAA, call 425–227–1221. FAA–2017–0126. language in paragraph (g) of the
(5) You may view this service information
Examining the AD Docket proposed AD to remove a reference to
that is incorporated by reference at the
National Archives and Records Parts 2 and 3 of the Accomplishment
You may examine the AD docket on Instructions of Boeing Alert Service
Administration (NARA). For information on the Internet at http://
the availability of this material at NARA, call Bulletin 737–53A1354, dated December
202–741–6030, or go to: http://
www.regulations.gov by searching for 2, 2016. Boeing noted that Group 1
www.archives.gov/federal-register/cfr/ibr- and locating Docket No. FAA–2017– airplanes are those that have exceeded
locations.html. 0126; or in person at the Docket their limit of validity, and that the
Management Facility between 9 a.m. inspections are not applicable to those
Issued in Renton, Washington, on June 19,
2017.
and 5 p.m., Monday through Friday, airplanes. Boeing stated that it believes
except Federal holidays. The AD docket the intent of paragraph (g) of the
John P. Piccola, Jr.,
contains this final rule, the regulatory proposed AD is for the operator to
Acting Manager, Transport Airplane evaluation, any comments received, and
Directorate, Aircraft Certification Service. obtain maintenance actions in
other information. The address for the accordance with a method approved by
[FR Doc. 2017–13763 Filed 7–3–17; 8:45 am]
Docket Office (phone: 800–647–5527) is the FAA. Boeing further pointed out
BILLING CODE 4910–13–P Docket Management Facility, U.S. that the language in paragraph (g) of the
Department of Transportation, Docket proposed AD allows operators to
Operations, M–30, West Building perform inspections in accordance with
DEPARTMENT OF TRANSPORTATION Ground Floor, Room W12–140, 1200 Boeing Alert Service Bulletin 737–
Federal Aviation Administration New Jersey Avenue SE., Washington, 53A1354, dated December 2, 2016,
DC 20590. rather than in accordance with
14 CFR Part 39 FOR FURTHER INFORMATION CONTACT: paragraph (j) of the proposed AD
Galib Abumeri, Aerospace Engineer, (obtaining an alternative method of
[Docket No. FAA–2017–0126; Directorate Airframe Branch, ANM–120L, FAA, Los
Identifier 2016–NM–211–AD; Amendment compliance).
Angeles Aircraft Certification Office
39–18943; AD 2017–13–13] We agree with the commenter’s
(ACO), 3960 Paramount Boulevard,
request for the reasons provided. We
RIN 2120–AA64 Lakewood, CA 90712–4137; phone:
have revised paragraph (g) of this AD to
562–627–5324; fax: 562–627–5210;
Airworthiness Directives; The Boeing clarify the appropriate actions for Group
email: galib.abumeri@faa.gov.
Company Airplanes 1 airplanes.
SUPPLEMENTARY INFORMATION:
AGENCY: Federal Aviation Request To Correct a Service Bulletin
Discussion Number
Administration (FAA), DOT.
ACTION: Final rule. We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR Boeing requested that we change two
SUMMARY: We are adopting a new part 39 by adding an AD that would sentences in paragraph (h) of the
sradovich on DSK3GMQ082PROD with RULES
airworthiness directive (AD) for certain apply to certain The Boeing Company proposed AD that refer to ‘‘Boeing Alert
The Boeing Company Model 737–100, Model 737–100, –200, –200C, –300, Service Bulletin 757–53A1354.’’ Boeing
–200, –200C, –300, –400, and –500 –400, and –500 series airplanes. The noted that the correct service bulletin
series airplanes. This AD was prompted NPRM published in the Federal number is ‘‘737–53A1354.’’
by reports of frame web cracking at Register on March 2, 2017 (82 FR We agree with the commenter’s
certain locations. This AD requires 12303) (‘‘the NPRM’’). The NPRM was request and have revised paragraph (h)
repetitive inspections in certain prompted by reports of frame web of this AD accordingly.
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Document Created: 2017-07-04 02:00:37
Document Modified: 2017-07-04 02:00:37
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective August 9, 2017. | |
| 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 | 82 FR 30958 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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