82 FR 24039 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 100 (May 25, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 100 (May 25, 2017)
| Page Range | 24039-24043 | |
| FR Document | 2017-10282 |
[Federal Register Volume 82, Number 100 (Thursday, May 25, 2017)] [Rules and Regulations] [Pages 24039-24043] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-10282] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-8849; Directorate Identifier 2015-NM-174-AD; Amendment 39-18892; AD 2017-10-18] 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 A330-223F, -223, -321, -322, and -323 airplanes. This AD was prompted by fatigue load analysis that determined the need for reduced inspection intervals and updated torque values of the bolts. This AD requires repetitive torque checks of the forward engine mount bolts, an inspection of the forward mount assembly, and replacement of the bolts or repair of the forward mount assembly as necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective June 29, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 29, 2017. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; 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- 8849. 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- 8849; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138; fax: 425-227-1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A330-223F, -223, -321, -322, and -323 airplanes. The NPRM published in the Federal Register on August 30, 2016 (81 FR 59535). The NPRM was prompted by fatigue load analysis that determined the need for reduced inspection intervals (for torque checks required by AD 2013-14-04, Amendment 39- 17509 (78 FR 68352, November 14, 2013) (``AD 2013-14-04'')) and updated torque values of the bolts. The NPRM proposed to require repetitive torque checks to determine if there are any loose or broken forward engine mount bolts, and, if necessary, replacement of all four forward engine mount bolts and associated nuts, inspection of the forward mount assembly, and repair. We are issuing this AD to detect and correct loose and broken bolts, which could lead to engine detachment in flight and damage to the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2015-0214, dated October 19, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A330-223F, -223, -321, -322, and -323 airplanes. The MCAI states: The forward mount engine pylon bolts, Part Number (P/N) 51U615, fitted on Airbus A330 aeroplanes with Pratt & Whitney (PW) PW4000 engines, are made from MP159 material. Analysis made by PW identified that MP159 material pylon bolts do not meet the full life cycle torque check interval requirement, in a bolt-out condition. Consequently, PW issued Alert Service Bulletin (ASB) PW4G-100-A71- 32, and the U.S. Federal Aviation Administration (FAA), as Engine Certification Authority, issued FAA AD 2006-16-05 [Amendment 39- 14705 (71 FR 44185, August 4, 2006) (``AD 2006-16-05'')] to require repetitive torque checks of MP159 material forward mount pylon bolts fitted on certain PW4000 series engines. However, the engine mount system is considered to be part of aeroplane certification rather than the engine certification. Following further fatigue load analysis by Airbus of the A330 engine mount system, it was determined that the torque check interval for MP159 material forward mount pylon bolts, as required by FAA AD 2006-16-05 (2,700 flight cycles (FC)), provided an insufficient level of safety for Airbus A330 aeroplanes. This condition, if not detected and corrected, could ultimately lead to detachment of the engine from the aeroplane, possibly resulting in damage to the aeroplane and/or injury to persons on the ground. Consequently, EASA issued AD 2012-0094 [which corresponds to FAA AD 2013-14-04] to require accomplishment of repetitive torque checks of the forward mount pylon bolts installed on affected A330 aeroplanes and, depending on findings, replacement of all four bolts and associated nuts, in accordance with PW ASB PW4G-100-A71-32 Revision 01 and Airbus Service Bulletin (SB) A330-71-3028. Since that AD was issued, it has been concluded that a new torque value must be applied. Consequently, Airbus issued SB A330-71-3028 Revision 02 and PW issued ASB PW4G-100-A71-32 Revision 02 to update the torque value. Additional forward mount inspections are also provided in case of one or more forward engine mount bolts is found loose, broken or missing. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2012-0094, which is superseded, introduces a new torque value, and requires additional inspections and, depending on findings, corrective action(s). Corrective actions include repetitive torque checks to determine if there are any loose or broken forward engine mount bolts on both engines, and, if necessary, replacement of all four forward engine mount bolts and associated nuts, inspection of the forward mount assembly, and repair. 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-2016-8849. Comments We gave the public the opportunity to participate in developing this AD. The [[Page 24040]] following presents the comments received on the NPRM and the FAA's response to each comment. Request To Correct Typographical Error American Airlines (AA) requested that we correct the reference to the FAA AD in paragraph (g)(1) of the proposed AD, which incorrectly identified AD 2013-13-05. The correct AD number for this terminating action is 2013-14-04. We agree and have revised paragraph (g)(1) of this AD accordingly. Request To Clarify Compliance Time AA requested that we clarify the compliance time for airplanes with an average flight time (AFT) of more than 132 minutes for the second cycle interval (1,851-2,700 flight cycles). AA proposed that we revise the second row of table 1 to paragraph (g) of the proposed AD by referring to the specified compliance times since accomplishing actions in AD 2013-14-04. We agree that clarification is necessary. The compliance times for the initial and repetitive torque checks required by AD 2013-14-04 are identified in table 1 to paragraph (g)(1) of this AD (table 1 to paragraph (g) of the proposed AD). The compliance times include specified flight cycles since the last torque check specified in Pratt & Whitney Alert Service Bulletin PW4G-100-A71-32, which operators might have accomplished to comply with AD 2013-14-04. Paragraph (g)(1) of this AD requires that the next torque check be done in accordance with Airbus Service Bulletin A330-71-3028, Revision 02, dated August 31, 2015 (``A330-71-3028, R02''). Accomplishment of the torque check required by paragraph (g)(1) of this AD terminates the requirements of AD 2013-14-04. We have not changed this AD regarding this issue. Request To Clarify Terminating Action Paragraph (h) of the proposed AD stated that accomplishment of the actions specified by paragraph (g) of the proposed AD ``constitutes compliance with'' the requirements specified in paragraph (g) of AD 2006-16-05. AA requested that we revise paragraph (h) of the proposed AD to specifically state that the new AD would also ``terminate'' the inspection specified in AD 2006-16-05. We agree with the commenter. We have revised paragraph (h) of this AD to state that accomplishment of the actions required by paragraph (g) of this AD terminates the requirements of paragraph (g) of AD 2006- 16-05. Request To Allow Use of Higher Torque Values AA requested that we revise paragraph (j) of the proposed AD to specifically allow early compliance with the AD upon its release and prior to the effective date of the AD, using Airbus Service Bulletin A330-71-3028, R02. AA stated that this would allow operators to immediately begin using the higher torque values specified in Airbus Service Bulletin A330-71-3028, R02. AA stated that as written, the AD would not allow operators to immediately use the higher torque values specified in Airbus Service Bulletin A330-71-3028, R02, because AD 2013-14-04 specifies the use of Airbus Service Bulletin A330-71-3028, Revision 01, dated February 12, 2012, which contains lower torque values. AA stated that this would preclude the need for a request for an alternative method of compliance (AMOC) against AD 2013-14-04 to allow the use of the higher torque values, and that this change would streamline the compliance revision process. We acknowledge the request and agree that clarification is necessary. Because AD 2013-14-04 requires using Airbus Service Bulletin A330-71-3028, Revision 01, dated February 12, 2012, operators need approval to use Airbus Service Bulletin A330-71-3028, R02, as an AMOC for the requirements of AD 2013-14-04. We have issued global AMOC ANM- 116-17-243, dated April 4, 2017, approving the use of Airbus Service Bulletin A330-71-3028, R02, for compliance with the requirements of AD 2013-14-04. Therefore, no changes to this AD are necessary regarding this issue. Request To Limit Requirements for Certain Approvals Delta Air Lines (Delta) requested that we revise the statement in paragraph (g)(2) of the proposed AD to remove the requirement to obtain FAA, EASA, or Airbus Design Organization Approval (DOA) approval for any instance where Airbus Service Bulletin A330-71-3028, R02, specifies contacting Airbus. Delta requested that we instead require these approvals only for damage that exceeds the allowable limits in the airplane maintenance manual (AMM); component maintenance manual (CMM); or cleaning, instruction and repair (CIR) manual. Delta stated that Airbus Service Bulletin A330-71-3028, R02, specifies contacting Airbus any time a bolt is found out of tolerance regardless whether any damage is found. As such, this would effectively require FAA, EASA, or Airbus DOA approval any time a bolt is found with a torque out of limits, even if there is no damage to the forward mount assembly, or if the damage is within the AMM, CMM, or CIR allowable limits. Delta agreed with the required approvals, but only when there is damage that exceeds those limits. Delta stated that this change would limit the number of AMOC requests, and reduce airplane out-of-service times while maintaining the acceptable level of safety. We disagree with the commenter's request to change the corrective action requirement in paragraph (g)(2) of this AD. The requirements of this AD correspond with those specified in the MCAI. The MCAI refers to Airbus Service Bulletin A330-71-3028, R02, which specifies that when any bolt is found with a torque out of limits, corrective actions must be done. We have determined that these actions are necessary to address the identified unsafe condition. However, under the provisions of paragraph (k)(1) of this AD, we will consider requests for approval of alternative corrective actions if sufficient data are submitted to substantiate that the alternative actions would provide an acceptable level of safety. We have not changed this AD regarding this issue. Request To Allow Replacement Instead of Repair Delta stated that paragraph (g)(2) of the proposed AD, which applies to the airplane (not the engine mount), would require repair before further flight. Delta interpreted this to mean the proposed AD would require repair of the forward engine mount before the airplane could return to flight. Delta requested that we revise the proposed AD to include a statement that explicitly allows replacement of damaged engine mounts, allowing the airplane to return to service as quickly as possible. We partially agree with the commenter's request. We agree that replacement of an affected forward engine mount might be allowed as a corrective action and that a different compliance time may be acceptable. We have revised paragraph (g)(2) of this AD by replacing the proposed requirement to repair before further flight with the requirement to contact the FAA, EASA, or Airbus's EASA DOA before further flight to obtain applicable corrective action instructions approved by the FAA, EASA, or Airbus's EASA DOA, and to do applicable corrective actions within the compliance time specified in those instructions. [[Page 24041]] Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A330-71-3028, Revision 02, dated August 31, 2015. The service information describes procedures for repetitive torque checks for loose or broken forward engine mount bolts on both engines, replacement of all four forward engine mount bolts and associated nuts, and inspection of the forward mount assembly. 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 41 airplanes of U.S. registry. We also estimate that it would take about 3 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts would cost about $6,747 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $287,082, or $7,002 per product. In addition, we estimate that any necessary follow-on actions would take about 1 work-hour and require parts costing $6,747, for a cost of $6,832 per product. We have no way of determining the number of aircraft that might need these actions. 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): 2017-10-18 Airbus: Amendment 39-18892; Docket No. FAA-2016-8849; Directorate Identifier 2015-NM-174-AD. (a) Effective Date This AD is effective June 29, 2017. (b) Affected ADs This AD affects AD 2006-16-05, Amendment 39-14705 (71 FR 44185, August 4, 2006) (``AD 2006-16-05''); and AD 2013-14-04, Amendment 39-17509 (78 FR 68352, November 14, 2013) (``AD 2013-14-04''). (c) Applicability This AD applies to Airbus Model A330-223F, -223, -321, -322, and -323 airplanes, certificated in any category, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) Reason This AD was prompted by fatigue load analysis that determined the need for certain reduced inspection intervals and updated torque values of the forward engine mount pylon bolts. We are issuing this AD to detect and correct loose or broken bolts, which could lead to engine detachment in flight and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Torque Check, Replacement, and Terminating Action for AD 2013-14-04 (1) At the applicable compliance time specified in table 1 to paragraph (g)(1) of this AD, do a torque check to determine if there are any loose or broken forward engine mount bolts (4 positions/ engine) on both engines, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-71-3028, Revision 02, dated August 31, 2015. Repeat the torque check at the applicable time intervals not to exceed the values specified in table 1 to paragraph (g)(1) of this AD. For the purposes of this AD, the average flight time (AFT) is defined as a computation of the number of flight hours divided by the number of flight cycles accumulated since the most recent torque check or since the airplane's first flight, as applicable. Accomplishment of the initial torque check required by this paragraph terminates the requirements of AD 2013- 14-04. [[Page 24042]] Table 1 to Paragraph (g)(1) of This AD ---------------------------------------------------------------------------------------------------------------- Flight cycles accumulated as of December 19, 2013 (the effective date of AD 2013-14-04), since last Airplane models torque check specified Compliance time Torque check interval in Pratt & Whitney (not to exceed) Alert Service Bulletin PW4G-100-A71-32 or since airplane's first flight, as applicable ---------------------------------------------------------------------------------------------------------------- Model A330-321, -322, and -323 0-1,850 Within 2,350 flight 2,350 flight cycles or airplanes with AFT more than 132 cycles since the last 24,320 flight hours, minutes; and Model A330-223 torque check as whichever occurs airplanes. specified in Pratt & first. Whitney Alert Service Bulletin PW4G-100-A71- 32, or since airplane's first flight, as applicable. Model A330-321, -322, and -323 1,851-2,700 Within 500 flight 2,350 flight cycles or airplanes with AFT more than 132 cycles after December 24,320 flight hours, minutes; and Model A330-223 19, 2013 (the whichever occurs airplanes. effective date of AD first. 2013-14-04), without exceeding 2,700 flight cycles since last torque check as specified in Pratt & Whitney Alert Service Bulletin PW4G-100-A71- 32, or since airplane's first flight, as applicable; or within 3 months after December 19, 2013; whichever occurs later. Model A330-321, -322, and -323 0-1,450 Within 1,950 flight 1,950 flight cycles or airplanes with AFT 132 minutes or cycles since the last 20,210 flight hours, less; and Model A330-321, -322, and - torque check performed whichever occurs 323 airplanes on which the AFT is as specified in Pratt first. not calculated on a regular basis. & Whitney Alert Service Bulletin PW4G- 100-A71-32, or since airplane's first flight, as applicable. Model A330-321, -322, and -323 1,451-2,700 Within 500 flight 1,950 flight cycles or airplanes with AFT 132 minutes or cycles after December 20,210 flight hours, less; and Model A330-321, -322, and 19, 2013 (the whichever occurs [dash]323 airplanes on which the AFT effective date of AD first. is not calculated on a regular basis. 2013-14-04), without exceeding 2,700 flight cycles since last torque check performed as specified in Pratt & Whitney Alert Service Bulletin PW4- 100-A71-32, or since airplane's first flight, as applicable; or within 3 months after December 19, 2013; whichever occurs later. Model A330-223F airplanes............ Any Within 2,140 flight 2,140 flight cycles or cycles or 6,600 flight 6,600 flight hours, hours, whichever whichever occurs occurs first since the first. last torque check performed as specified in Pratt & Whitney Alert Service Bulletin PW4G-100-A71-32, or since airplane's first flight, as applicable. ---------------------------------------------------------------------------------------------------------------- (2) If any loose or broken bolt is detected during the check required by paragraph (g)(1) of this AD, before further flight, do the actions specified by paragraphs (g)(2)(i) and (g)(2)(ii) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-71-3028, Revision 02, dated August 31, 2015; except, where the service information specifies to contact the manufacturer for further corrective actions, before further flight contact 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); to obtain applicable corrective action instructions approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA; and accomplish the applicable corrective actions within the compliance time specified in those instructions. (i) Replace all four forward engine mount bolts and associated nuts, on the engine where the loose or broken bolt was detected, with new bolts and nuts. (ii) Do nondestructive inspections of the forward mount assembly for damage including cracks, dents, nicks, and scratches, and do all applicable corrective actions. (3) Replacement of bolts and nuts as required by paragraph (g)(2)(i) of this AD is not terminating action for the repetitive torque checks required by paragraph (g)(1) of this AD. (h) Terminating Action for Paragraph (g) of AD 2006-16-05 Accomplishment of the actions required by paragraph (g) of this AD terminates the requirements specified in paragraph (g) of AD 2006-16-05. (i) Parts Installation Prohibition As of December 19, 2013 (the effective date of AD 2013-14-04), no person may install, on any airplane, any forward mount pylon bolt made of INCO718 material and having Pratt & Whitney part number 54T670. (j) Credit for Previous Actions This paragraph provides credit for the actions required by paragraphs (g)(1) and (g)(2)(i) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A330-71-3028, dated December 16, 2011, or Airbus Service Bulletin A330-71-3028, Revision 01, dated February 20, 2012. (k) 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138; fax: 425-227-1149. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: 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 [[Page 24043]] 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 (g)(2) of this AD: If any 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 or 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 an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2015-0214, dated October 19, 2015, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-8849. (2) For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138; fax: 425-227-1149. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (m)(4) of this AD. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A330-71-3028, Revision 02, dated August 31, 2015. (ii) Reserved. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email [email protected]; Internet http://www.airbus.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on May 8, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-10282 Filed 5-24-17; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations 24039
Issued in Renton, Washington, on May 10, Examining the AD Docket A330 aeroplanes with Pratt & Whitney (PW)
2017. PW4000 engines, are made from MP159
You may examine the AD docket on material. Analysis made by PW identified
Michael Kaszycki,
the Internet at http:// that MP159 material pylon bolts do not meet
Acting Manager, Transport Airplane www.regulations.gov by searching for the full life cycle torque check interval
Directorate, Aircraft Certification Service. and locating Docket No. FAA–2016– requirement, in a bolt-out condition.
[FR Doc. 2017–10266 Filed 5–24–17; 8:45 am] 8849; or in person at the Docket Consequently, PW issued Alert Service
BILLING CODE 4910–13–P Management Facility between 9 a.m. Bulletin (ASB) PW4G–100–A71–32, and the
and 5 p.m., Monday through Friday, U.S. Federal Aviation Administration (FAA),
except Federal holidays. The AD docket as Engine Certification Authority, issued
DEPARTMENT OF TRANSPORTATION FAA AD 2006–16–05 [Amendment 39–14705
contains this AD, the regulatory (71 FR 44185, August 4, 2006) (‘‘AD 2006–
evaluation, any comments received, and 16–05’’)] to require repetitive torque checks
Federal Aviation Administration
other information. The address for the of MP159 material forward mount pylon
Docket Office (telephone 800–647–5527) bolts fitted on certain PW4000 series engines.
14 CFR Part 39
is Docket Management Facility, U.S. However, the engine mount system is
Department of Transportation, Docket considered to be part of aeroplane
[Docket No. FAA–2016–8849; Directorate Operations, M–30, West Building certification rather than the engine
Identifier 2015–NM–174–AD; Amendment Ground Floor, Room W12–140, 1200 certification. Following further fatigue load
39–18892; AD 2017–10–18] New Jersey Avenue SE., Washington, analysis by Airbus of the A330 engine mount
system, it was determined that the torque
DC 20590. check interval for MP159 material forward
RIN 2120–AA64 FOR FURTHER INFORMATION CONTACT: mount pylon bolts, as required by FAA AD
Vladimir Ulyanov, Aerospace Engineer, 2006–16–05 (2,700 flight cycles (FC)),
Airworthiness Directives; Airbus International Branch, ANM–116, provided an insufficient level of safety for
Airplanes Transport Airplane Directorate, FAA, Airbus A330 aeroplanes.
1601 Lind Avenue SW., Renton, WA This condition, if not detected and
AGENCY: Federal Aviation
98057–3356; telephone: 425–227–1138; corrected, could ultimately lead to
Administration (FAA), Department of detachment of the engine from the aeroplane,
Transportation (DOT). fax: 425–227–1149.
possibly resulting in damage to the aeroplane
SUPPLEMENTARY INFORMATION: and/or injury to persons on the ground.
ACTION: Final rule.
Discussion Consequently, EASA issued AD 2012–0094
SUMMARY: We are adopting a new [which corresponds to FAA AD 2013–14–04]
airworthiness directive (AD) for all We issued a notice of proposed to require accomplishment of repetitive
rulemaking (NPRM) to amend 14 CFR torque checks of the forward mount pylon
Airbus Model A330–223F, –223, –321,
part 39 by adding an AD that would bolts installed on affected A330 aeroplanes
–322, and –323 airplanes. This AD was
apply to all Airbus Model A330–223F, and, depending on findings, replacement of
prompted by fatigue load analysis that all four bolts and associated nuts, in
–223, –321, –322, and –323 airplanes.
determined the need for reduced accordance with PW ASB PW4G–100–A71–
The NPRM published in the Federal
inspection intervals and updated torque 32 Revision 01 and Airbus Service Bulletin
Register on August 30, 2016 (81 FR
values of the bolts. This AD requires (SB) A330–71–3028.
59535). The NPRM was prompted by
repetitive torque checks of the forward Since that AD was issued, it has been
fatigue load analysis that determined concluded that a new torque value must be
engine mount bolts, an inspection of the
the need for reduced inspection applied.
forward mount assembly, and
intervals (for torque checks required by Consequently, Airbus issued SB A330–71–
replacement of the bolts or repair of the
AD 2013–14–04, Amendment 39–17509 3028 Revision 02 and PW issued ASB
forward mount assembly as necessary.
(78 FR 68352, November 14, 2013) (‘‘AD PW4G–100–A71–32 Revision 02 to update
We are issuing this AD to address the the torque value. Additional forward mount
2013–14–04’’)) and updated torque
unsafe condition on these products. inspections are also provided in case of one
values of the bolts. The NPRM proposed
DATES: This AD is effective June 29, to require repetitive torque checks to or more forward engine mount bolts is found
2017. loose, broken or missing.
determine if there are any loose or For the reasons described above, this
The Director of the Federal Register broken forward engine mount bolts, [EASA] AD retains the requirements of EASA
approved the incorporation by reference and, if necessary, replacement of all four AD 2012–0094, which is superseded,
of a certain publication listed in this AD forward engine mount bolts and introduces a new torque value, and requires
as of June 29, 2017. associated nuts, inspection of the additional inspections and, depending on
ADDRESSES: For service information forward mount assembly, and repair. findings, corrective action(s).
identified in this final rule, contact We are issuing this AD to detect and Corrective actions include repetitive
Airbus SAS, Airworthiness Office— correct loose and broken bolts, which torque checks to determine if there are
EAL, 1 Rond Point Maurice Bellonte, could lead to engine detachment in any loose or broken forward engine
31707 Blagnac Cedex, France; telephone flight and damage to the airplane. mount bolts on both engines, and, if
+33 5 61 93 36 96; fax +33 5 61 93 45 The European Aviation Safety Agency necessary, replacement of all four
80; email airworthiness.A330-A340@ (EASA), which is the Technical Agent forward engine mount bolts and
airbus.com; Internet http:// for the Member States of the European associated nuts, inspection of the
www.airbus.com. You may view this Union, has issued EASA AD 2015–0214, forward mount assembly, and repair.
referenced service information at the dated October 19, 2015 (referred to after You may examine the MCAI in the AD
FAA, Transport Airplane Directorate, this as the Mandatory Continuing docket on the Internet at http://
1601 Lind Avenue SW., Renton, WA. Airworthiness Information, or ‘‘the www.regulations.gov by searching for
For information on the availability of MCAI’’), to correct an unsafe condition and locating Docket No. FAA–2016–
this material at the FAA, call 425–227– for all Airbus Model A330–223F, –223, 8849.
1221. It is also available on the Internet –321, –322, and –323 airplanes. The
at http://www.regulations.gov by MCAI states: Comments
searching for and locating Docket No. The forward mount engine pylon bolts, We gave the public the opportunity to
FAA–2016–8849. Part Number (P/N) 51U615, fitted on Airbus participate in developing this AD. The
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![Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations 24041
Conclusion the FAA Administrator. ‘‘Subtitle VII: § 39.13 [Amended]
We reviewed the available data, Aviation Programs,’’ describes in more
detail the scope of the Agency’s ■ 2. The FAA amends § 39.13 by adding
including the comments received, and the following new airworthiness
determined that air safety and the authority.
We are issuing this rulemaking under directive (AD):
public interest require adopting this AD
with the changes described previously the authority described in ‘‘Subtitle VII, 2017–10–18 Airbus: Amendment 39–18892;
Part A, Subpart III, Section 44701: Docket No. FAA–2016–8849; Directorate
and minor editorial changes. We have
General requirements.’’ Under that Identifier 2015–NM–174–AD.
determined that these changes:
• Are consistent with the intent that section, Congress charges the FAA with (a) Effective Date
was proposed in the NPRM for promoting safe flight of civil aircraft in
This AD is effective June 29, 2017.
correcting the unsafe condition; and air commerce by prescribing regulations
• Do not add any additional burden for practices, methods, and procedures (b) Affected ADs
upon the public than was already the Administrator finds necessary for This AD affects AD 2006–16–05,
proposed in the NPRM. safety in air commerce. This regulation Amendment 39–14705 (71 FR 44185, August
We also determined that these is within the scope of that authority 4, 2006) (‘‘AD 2006–16–05’’); and AD 2013–
changes will not increase the economic because it addresses an unsafe condition 14–04, Amendment 39–17509 (78 FR 68352,
burden on any operator or increase the that is likely to exist or develop on November 14, 2013) (‘‘AD 2013–14–04’’).
scope of this AD. products identified in this rulemaking (c) Applicability
action.
Related Service Information Under 1 This AD applies to Airbus Model A330–
CFR Part 51 Regulatory Findings 223F, –223, –321, –322, and –323 airplanes,
certificated in any category, all manufacturer
Airbus has issued Service Bulletin We determined that this AD will not serial numbers.
A330–71–3028, Revision 02, dated have federalism implications under
August 31, 2015. The service Executive Order 13132. This AD will (d) Subject
information describes procedures for not have a substantial direct effect on Air Transport Association (ATA) of
repetitive torque checks for loose or the States, on the relationship between America Code 71, Powerplant.
broken forward engine mount bolts on the national government and the States,
(e) Reason
both engines, replacement of all four or on the distribution of power and
forward engine mount bolts and responsibilities among the various This AD was prompted by fatigue load
levels of government. analysis that determined the need for certain
associated nuts, and inspection of the
reduced inspection intervals and updated
forward mount assembly. This service For the reasons discussed above, I
torque values of the forward engine mount
information is reasonably available certify that this AD: pylon bolts. We are issuing this AD to detect
because the interested parties have 1. Is not a ‘‘significant regulatory and correct loose or broken bolts, which
access to it through their normal course action’’ under Executive Order 12866; could lead to engine detachment in flight and
of business or by the means identified 2. Is not a ‘‘significant rule’’ under the damage to the airplane.
in the ADDRESSES section. DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); (f) Compliance
Costs of Compliance 3. Will not affect intrastate aviation in Comply with this AD within the
We estimate that this AD affects 41 Alaska; and compliance times specified, unless already
airplanes of U.S. registry. 4. Will not have a significant done.
We also estimate that it would take economic impact, positive or negative, (g) Torque Check, Replacement, and
about 3 work-hours per product to on a substantial number of small entities Terminating Action for AD 2013–14–04
comply with the basic requirements of under the criteria of the Regulatory (1) At the applicable compliance time
this AD. The average labor rate is $85 Flexibility Act. specified in table 1 to paragraph (g)(1) of this
per work-hour. Required parts would AD, do a torque check to determine if there
cost about $6,747 per product. Based on List of Subjects in 14 CFR Part 39
are any loose or broken forward engine
these figures, we estimate the cost of Air transportation, Aircraft, Aviation mount bolts (4 positions/engine) on both
this AD on U.S. operators to be safety, Incorporation by reference, engines, in accordance with the
$287,082, or $7,002 per product. Safety. Accomplishment Instructions of Airbus
In addition, we estimate that any Service Bulletin A330–71–3028, Revision 02,
necessary follow-on actions would take Adoption of the Amendment dated August 31, 2015. Repeat the torque
about 1 work-hour and require parts Accordingly, under the authority check at the applicable time intervals not to
costing $6,747, for a cost of $6,832 per delegated to me by the Administrator, exceed the values specified in table 1 to
the FAA amends 14 CFR part 39 as paragraph (g)(1) of this AD. For the purposes
product. We have no way of
of this AD, the average flight time (AFT) is
determining the number of aircraft that follows:
defined as a computation of the number of
might need these actions. flight hours divided by the number of flight
PART 39—AIRWORTHINESS
Authority for This Rulemaking cycles accumulated since the most recent
DIRECTIVES torque check or since the airplane’s first
Title 49 of the United States Code flight, as applicable. Accomplishment of the
specifies the FAA’s authority to issue ■ 1. The authority citation for part 39
initial torque check required by this
rules on aviation safety. Subtitle I, continues to read as follows: paragraph terminates the requirements of AD
section 106, describes the authority of Authority: 49 U.S.C. 106(g), 40113, 44701. 2013–14–04.
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![Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations 24043
the Manager, International Branch, ANM– Issued in Renton, Washington, on May 8, and locating Docket No. FAA–2016–
116, Transport Airplane Directorate, FAA; or 2017. 9431; or in person at the Docket
EASA; or Airbus’s EASA DOA. If approved Michael Kaszycki, Management Facility between 9 a.m.
by the DOA, the approval must include the Acting Manager, Transport Airplane and 5 p.m., Monday through Friday,
DOA-authorized signature. Directorate, Aircraft Certification Service. except Federal holidays. The AD docket
(3) Required for Compliance (RC): Except
[FR Doc. 2017–10282 Filed 5–24–17; 8:45 am] contains this AD, the regulatory
as required by paragraph (g)(2) of this AD: If
any service information contains procedures BILLING CODE 4910–13–P evaluation, any comments received, and
or tests that are identified as RC, those other information. The street address for
procedures and tests must be done to comply the Docket Office (telephone 800–647–
with this AD; any procedures or tests that are DEPARTMENT OF TRANSPORTATION 5527) is Docket Management Facility,
not identified as RC are recommended. Those U.S. Department of Transportation,
procedures and tests that are not identified Federal Aviation Administration Docket Operations, M–30, West
as RC may be deviated from using accepted Building Ground Floor, Room W12–140,
methods in accordance with the operator’s 14 CFR Part 39 1200 New Jersey Avenue SE.,
maintenance or inspection program without Washington, DC 20590.
obtaining approval of an AMOC, provided [Docket No. FAA–2016–9431; Directorate
Identifier 2016–NM–104–AD; Amendment FOR FURTHER INFORMATION CONTACT:
the procedures and tests identified as RC can
39–18897; AD 2017–10–23] Sanjay Ralhan, Aerospace Engineer,
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
International Branch, ANM–116,
RIN 2120–AA64 Transport Airplane Directorate, FAA,
changes to procedures or tests identified as
RC require approval of an AMOC. Airworthiness Directives; Airbus 1601 Lind Avenue SW., Renton, WA
Airplanes 98057–3356; telephone 425–227–1405;
(l) Related Information fax 425–227–1149.
(1) Refer to Mandatory Continuing AGENCY: Federal Aviation SUPPLEMENTARY INFORMATION:
Airworthiness Information (MCAI) EASA AD Administration (FAA), Department of
2015–0214, dated October 19, 2015, for Discussion
Transportation (DOT).
related information. This MCAI may be We issued a notice of proposed
found in the AD docket on the Internet at ACTION: Final rule.
rulemaking (NPRM) to amend 14 CFR
http://www.regulations.gov by searching for
and locating Docket No. FAA–2016–8849. SUMMARY: We are adopting a new part 39 by adding an AD that would
(2) For more information about this AD, airworthiness directive (AD) for certain apply to certain Airbus Model A321
contact Vladimir Ulyanov, Aerospace Airbus Model A321 series airplanes. series airplanes. The NPRM published
Engineer, International Branch, ANM–116, This AD was prompted by a in the Federal Register on December 2,
Transport Airplane Directorate, FAA, 1601 determination that cracks could develop 2016 (81 FR 86975). The NPRM was
Lind Avenue SW., Renton, WA 98057–3356; on holes at certain fuselage frame prompted by a determination from
telephone: 425–227–1138; fax: 425–227– locations. This AD requires repetitive fatigue testing on the Model A321
1149. inspections for cracking on holes at airframe that cracks could develop on
(3) Service information identified in this certain fuselage frame locations, and holes at certain fuselage frame locations.
AD that is not incorporated by reference is The NPRM proposed to require
repairs if necessary. We are issuing this
available at the addresses specified in
AD to address the unsafe condition on repetitive inspections for cracking on
paragraphs (m)(3) and (m)(4) of this AD.
these products. holes at certain fuselage frame locations,
(m) Material Incorporated by Reference and repairs if necessary. We are issuing
DATES: This AD is effective June 29,
(1) The Director of the Federal Register 2017. this AD to detect and correct cracking at
approved the incorporation by reference The Director of the Federal Register certain hole locations in the fuselage
(IBR) of the service information listed in this approved the incorporation by reference frame, which could result in reduced
paragraph under 5 U.S.C. 552(a) and 1 CFR structural integrity of the airplane.
part 51.
of certain publications listed in this AD
as of June 29, 2017. The European Aviation Safety Agency
(2) You must use this service information (EASA), which is the Technical Agent
as applicable to do the actions required by ADDRESSES: For service information
for the Member States of the European
this AD, unless this AD specifies otherwise. identified in this final rule, contact Union, has issued EASA Airworthiness
(i) Airbus Service Bulletin A330–71–3028, Airbus, Airworthiness Office—EIAS, 1
Revision 02, dated August 31, 2015. Directive 2016–0106, dated June 6, 2016
Rond Point Maurice Bellonte, 31707 (referred to after this as the Mandatory
(ii) Reserved. Blagnac Cedex, France; telephone +33 5 Continuing Airworthiness Information,
(3) For service information identified in
61 93 36 96; fax +33 5 61 93 44 51; email or ‘‘the MCAI’’), to correct an unsafe
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
account.airworth-eas@airbus.com; condition on certain Airbus Model A321
31707 Blagnac Cedex, France; telephone +33 Internet http://www.airbus.com. You series airplanes. The MCAI states:
5 61 93 36 96; fax +33 5 61 93 45 80; email may view this referenced service
information at the FAA, Transport Following a new full scale fatigue test
airworthiness.A330-A340@airbus.com;
Internet http://www.airbus.com. Airplane Directorate, 1601 Lind Avenue campaign on the A321 airframe, in the
context of the A321 extended service goal, it
(4) You may view this service information SW., Renton, WA. For information on was identified that cracks could develop on
at the FAA, Transport Airplane Directorate, the availability of this material at the holes at frame (FR) 35.2A between stringers
1601 Lind Avenue SW., Renton, WA. For FAA, call 425–227–1221. It is also (STR) 22 and STR 23 on right hand (RH) and
information on the availability of this available on the Internet at http:// left hand (LH) sides, also on aeroplanes
material at the FAA, call 425–227–1221. www.regulations.gov by searching for operated in the context of design service goal.
(5) You may view this service information This condition, if not detected and
that is incorporated by reference at the
and locating Docket No. FAA–2016–
9431. corrected, could reduce the structural
National Archives and Records integrity of the fuselage.
Administration (NARA). For information on Examining the AD Docket Prompted by these findings, Airbus
the availability of this material at NARA, call developed an inspection programme,
202–741–6030, or go to http:// You may examine the AD docket on published in Service Bulletin (SB) A320–53–
www.archives.gov/federal-register/cfr/ibr- the Internet at http:// 1315 and SB A320–53–1316, each containing
locations.html. www.regulations.gov by searching for instructions for a different location.
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Document Created: 2018-11-08 08:53:06
Document Modified: 2018-11-08 08:53:06
| 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 June 29, 2017. | |
| Contact | Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138; fax: 425-227-1149. | |
| FR Citation | 82 FR 24039 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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