81 FR 34287 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 104 (May 31, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 104 (May 31, 2016)
| Page Range | 34287-34290 | |
| FR Document | 2016-12593 |
[Federal Register Volume 81, Number 104 (Tuesday, May 31, 2016)] [Proposed Rules] [Pages 34287-34290] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-12593] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-6896; Directorate Identifier 2016-NM-016-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A318-111, and -112 airplanes, Model A319-111, -112, -113, -114, and -115 airplanes, Model A320-211, -212 and -214 airplanes, and Model A321-111, -112, -211, -212, and -213 airplanes. This proposed AD was prompted by a report of a production quality deficiency on the inner retainer installed on link assemblies of the engine mount, which could result in failure of the retainer. This proposed AD would require an inspection for, and replacement of, all non-conforming aft engine mount retainers. We are proposing this AD to detect and correct non- conforming retainers of the aft engine mount. This condition could result in the loss of the locking feature of the nuts of the inner and outer pins; loss of the pins will result in the aft mount engine link no longer being secured to the aft engine mount, possibly resulting in damage to the airplane and injury to persons on the ground. DATES: We must receive comments on this proposed AD by July 15, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. [[Page 34288]] Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For Airbus service information identified in this NPRM, 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. For Goodrich service information identified in this NPRM, contact Goodrich Corporation, Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098; telephone: 619-691-2719; email: [email protected]; Internet: http://www.goodrich.com/TechPubs. 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. 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- 6896; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. 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: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-6896; Directorate Identifier 2016-NM-016-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2016-0010R1, dated February 16, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A318-111, and -112 airplanes, Model A319-111, -112, -113, -114, and - 115 airplanes, Model A320-211, -212, and -214 airplanes, and Model A321-111, -112, -211, -212, and -213 airplanes. The MCAI states: During in-service inspections, several aft engine mount inner retainers, fitted on aeroplanes equipped with CFM56-5A/5B engines, have been found broken. The results of the initial investigations highlighted that two different types of surface finish had been applied (respectively bright and dull material finishes), and that dull finish affects the strength of the retainer with regard to fatigue properties of the part. The pins which attach the engine link to the aft mount are secured by two nuts, which do not have a self-locking feature; this function is provided by the retainer brackets. In case of failure of the retainer bracket, the locking feature of the nuts of the inner and outer pins is lost; as a result, these nuts could subsequently become loose. In case of full loss of the nuts, there is the potential to also lose the pins, in which case the aft mount link will no longer be secured to the aft engine mount. The same locking feature is used for the three link assemblies of the aft mount. This condition, if not detected and corrected, could lead to in- flight loss of an aft mount link, possibly resulting in damage to the aeroplane and/or injury to persons on the ground. To address this potential unsafe condition, EASA issued AD 2013- 0050 [http://ad.easa.europa.eu/blob/easa_ad_2013_0050_superseded.pdf/AD_2013-0050_1] [which corresponds to FAA AD 2014-14-06, Amendment 39-17901 (79 FR 42655, July 23, 2014)] to require a detailed inspection (DET) of the aft engine mount inner retainers and the replacement of all retainers with dull finish with retainers having a bright finish. Since that [EASA] AD was issued, inspection results showed that the main cause of crack initiation remains the vibration dynamic effect that affects both retainers, either with ``dull'' or ``bright'' surface finishes. The non-conforming ``dull'' surface's pitting is an aggravating factor. Consequently, EASA issued AD 2015-0021 [http://ad.easa.europa.eu/blob/EASA_AD_2015_0021_superseded.pdf/AD_2015-0021_1] [which corresponds to FAA NPRM Docket No. FAA-2015-3632; Directorate Identifier 2015-NM-023-AD (80 FR 55798, September 7, 2015)], retaining the requirements of EASA AD 2013-0050, which was superseded, and requiring repetitive DET of all aft engine mount inner retainers and, depending on findings, their replacement. Since that [EASA] AD was issued, a production quality deficiency was identified by Airbus and UTAS (formerly Goodrich Aerostructures, the engine mount retainer manufacturer) on the delivery of the inner retainer, Part Number (P/N) 238-0252-505, installed in the three Link assemblies of the engine mount fitted on CFM56-5A/5B engines. Airbus issued AOT A71N011-15 and SB A320-71-1070 providing a list of affected parts and applicable corrective actions. Consequently, EASA issued [a new] AD * * *, retaining the requirements of EASA AD 2015-0021, which was superseded, and in addition requiring the identification and replacement of all non- conforming aft engine mount inner retainers. Since that [new EASA] AD was issued, AOT A71N011-15 was revised, removing errors and reducing the list of affected parts. For the reason described above, this [EASA] AD is revised, adding reference to the revised AOT, and removing [EASA] AD appendixes, which content is included in the referenced Airbus documentation. This [EASA] AD is still considered to be an interim action, pending development and availability of a final solution. This proposed AD would require an inspection for, and replacement of, all non-conforming aft engine mount retainers. 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-2016-6896. Related Service Information Under 1 CFR Part 51 We reviewed the following service information. This service information describes procedures for replacement of all non-conforming aft engine mount retainers. Airbus Service Bulletin A320-71-1070, dated November 23, 2015. This service information also describes procedures for an inspection for non-conforming aft engine mount retainers. Airbus Alert Operators Transmission (AOT) A71N011-15, Revision 01, dated February 1, 2016. Goodrich Service Bulletin RA32071-165, dated October 9, 2015. 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. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation [[Page 34289]] in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Costs of Compliance We estimate that this proposed AD affects 959 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product Cost on U.S. operators ---------------------------------------------------------------------------------------------------------------- Inspection..................... 4 work-hours x $85 per $0 $340 Up to $326,060. hour = $340. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary replacements that would be required based on the results of the proposed inspection. We have no way of determining the number of airplanes that might need these replacements: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Replacement......................... Up to 36 work-hours x $85 $10,000 Up to $13,060. per hour = $3,060. ---------------------------------------------------------------------------------------------------------------- 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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): Airbus: Docket No. FAA-2016-6896; Directorate Identifier 2016-NM- 016-AD. (a) Comments Due Date We must receive comments by July 15, 2016. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A318-111 and -112 airplanes. (2) Airbus Model A319-111, -112, -113, -114, and -115 airplanes. (3) Airbus Model A320-211, -212, and -214 airplanes. (4) Airbus Model A321-111, -112, -211, -212, and -213 airplanes. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) Reason This AD was prompted by a report of a production quality deficiency on the inner retainer installed on link assemblies of the engine mount, which could result in failure of the retainer. We are issuing this AD to detect and correct non-conforming retainers of the aft engine mount. This condition could result in loss of the locking feature of the nuts of the inner and outer pins; loss of the pins will result in the aft mount engine link no longer being secured to the aft engine mount, possibly resulting in damage to the airplane and injury to persons on the ground. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection and Replacement Within 2 months after the effective date of this AD, do an inspection to determine the part number of each engine mount inner retainer; and within 2 months after the effective date of this AD, replace each part that meets any of the criteria specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. Do the inspection in accordance with the service information specified in paragraph (h)(1) of this AD. Do the replacement in accordance with the service information specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD. A review of airplane maintenance records is acceptable in lieu of the inspection required by this paragraph, if the part [[Page 34290]] number of the engine mount inner retainer can be conclusively determined from that review. (1) An aft engine mount having a serial number listed in table 1 of Airbus Alert Operators Transmission (AOT) A71N011-15, Rev 01, dated February 1, 2016. (2) An engine mount inner retainer installed on an airplane between the first flight of the airplane or March 1, 2015 (whichever occurs later), and the effective date of this AD, and that can be identified by a purchase order (PO) listed in table 2 of Airbus AOT A71N011-15, Rev 01, dated February 1, 2016. (3) An engine mount inner retainer installed on an airplane between the first flight of the airplane or March 1, 2015 (whichever occurs later), and the effective date of this AD, and that cannot be identified by a PO. (h) Service Information for Actions Required by Paragraph (g) of This AD Accomplish the replacement required by paragraph (g) of this AD in accordance with the service information specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD. (1) The Accomplishment Instructions of Airbus Service Bulletin A320-71-1070, dated November 23, 2015. (2) Paragraph 4.2.2, ``Requirements,'' of Airbus AOT A71N011-15, Revision 01, dated February 1, 2016. (3) The Accomplishment Instructions of Goodrich Service Bulletin RA32071-165, dated October 9, 2015. (i) Credit for Previous Actions This paragraph provides credit for the applicable actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus AOT A71N011-15, Revision 01, dated February 1, 2016, which is not incorporated by reference in this AD. (j) Parts Installation Prohibition As of the effective date of this AD, no person may install any part that meets any of the criteria specified in paragraph (j)(1), (j)(2), (j)(3) of this AD on any airplane. (1) An aft engine mount having a serial number listed in table 1 of Airbus AOT A71N011-15, Rev 01, dated February 1, 2016. (2) An engine mount inner retainer delivered through a PO listed in table 2 of Airbus AOT A71N011-15, Rev 01, dated February 1, 2016. (3) An engine mount inner retainer delivered through an unidentified PO. (k) Special Flight Permits Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed. (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone: 425-227-1405; fax: 425-227-1149. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: 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 European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): 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. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016-0010R1, dated February 16, 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-2016-6896. (2) For Airbus 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. For Goodrich service information identified in this AD, contact Goodrich Corporation, Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098; telephone: 619-691- 2719; email: [email protected]; Internet: http://www.goodrich.com/TechPubs. 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. Issued in Renton, Washington, on May 20, 2016. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-12593 Filed 5-27-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 104 / Tuesday, May 31, 2016 / Proposed Rules 34287
hooks and the eccentric bush at FR60 In accordance with 14 CFR 39.19, send your Issued in Renton, Washington, on May 18,
through FR64A. If any value outside request to your principal inspector or local 2016.
tolerance is found, adjust the latching hook Flight Standards District Office, as Dionne Palermo,
before further flight. appropriate. If sending information directly Acting Manager, Transport Airplane
(2) Do a one-time detailed inspection to to the International Branch, send it to ATTN: Directorate, Aircraft Certification Service.
detect signs of wear of the hooks, eccentric Dan Rodina, Aerospace Engineer,
bushes, and x-stops. If any wear is found, do [FR Doc. 2016–12522 Filed 5–27–16; 8:45 am]
International Branch, ANM–116, Transport
all applicable corrective actions before Airplane Directorate, FAA, 1601 Lind BILLING CODE 4910–13–P
further flight. Avenue SW., Renton, WA 98057–3356;
(3) Do a high frequency eddy current telephone 425–227–2125; fax 425–227–1149.
(HFEC) inspection to detect cracking at all Information may be emailed to: 9-ANM-116- DEPARTMENT OF TRANSPORTATION
frame fork stations of the aft LDCD. If any
AMOC-REQUESTS@faa.gov. Before using
crack is found, replace the cracked frame fork Federal Aviation Administration
any approved AMOC, notify your appropriate
before further flight. Repeat the HFEC
inspection thereafter at intervals not to principal inspector, or lacking a principal
inspector, the manager of the local flight 14 CFR Part 39
exceed 600 flight cycles.
standards district office/certificate holding [Docket No. FAA–2016–6896; Directorate
(h) Compliance Times district office. The AMOC approval letter Identifier 2016–NM–016–AD]
At the later of the times specified in must specifically reference this AD.
paragraphs (h)(1) and (h)(2) of this AD, do the (2) Contacting the Manufacturer: For any RIN 2120–AA64
actions required by paragraph (g) of this AD. requirement in this AD to obtain corrective
(1) Before the accumulation of 4,500 total actions from a manufacturer, the action must Airworthiness Directives; Airbus
flight cycles. be accomplished using a method approved Airplanes
(2) At the applicable time specified by by the Manager, International Branch, ANM–
paragraph (h)(2)(i) or (h)(2)(ii) of this AD. 116, Transport Airplane Directorate, FAA; or AGENCY: Federal Aviation
(i) For airplanes that have accumulated the European Aviation Safety Agency Administration (FAA), DOT.
8,000 or more total flight cycles as of the (EASA); or Airbus’s EASA Design ACTION: Notice of proposed rulemaking
effective date this AD: Within 100 flight Organization Approval (DOA). If approved by (NPRM).
cycles after the effective date of this AD. the DOA, the approval must include the
(ii) For airplanes that have accumulated DOA-authorized signature. SUMMARY: We propose to adopt a new
fewer than 8,000 total flight cycles as of the (3) Reporting Requirements: A federal airworthiness directive (AD) for all
effective date of this AD: Within 400 flight agency may not conduct or sponsor, and a Airbus Model A318–111, and –112
cycles after the effective date of this AD. person is not required to respond to, nor airplanes, Model A319–111, –112, –113,
(i) Reporting shall a person be subject to a penalty for –114, and –115 airplanes, Model A320–
At the applicable time specified in failure to comply with a collection of 211, –212 and –214 airplanes, and
paragraph (i)(1) or (i)(2) of this AD, report the information subject to the requirements of Model A321–111, –112, –211, –212, and
findings (both positive and negative) of the the Paperwork Reduction Act unless that
–213 airplanes. This proposed AD was
clearance check and detailed inspection collection of information displays a current
valid OMB Control Number. The OMB
prompted by a report of a production
required by paragraphs (g)(1) and (g)(2) of quality deficiency on the inner retainer
this AD, and each HFEC inspection required Control Number for this information
by paragraph (g)(3) of this AD. Send the collection is 2120–0056. Public reporting for installed on link assemblies of the
report to Airbus in accordance with this collection of information is estimated to engine mount, which could result in
paragraph 7 of Airbus AOT A52W011–15, be approximately 5 minutes per response, failure of the retainer. This proposed AD
Revision 00, dated July 23, 2015. The report including the time for reviewing instructions, would require an inspection for, and
must include the applicable information completing and reviewing the collection of replacement of, all non-conforming aft
specified in Appendix 2 of Airbus AOT information. All responses to this collection engine mount retainers. We are
A52W011–15, Revision 00, dated July 23, of information are mandatory. Comments proposing this AD to detect and correct
2015. concerning the accuracy of this burden and non-conforming retainers of the aft
(1) If the inspection was done on or after suggestions for reducing the burden should engine mount. This condition could
the effective date of this AD: Submit the be directed to the FAA at: 800 Independence
report within 60 days after the inspection. result in the loss of the locking feature
Ave. SW., Washington, DC 20591, Attn:
(2) If the inspection was done before the Information Collection Clearance Officer, of the nuts of the inner and outer pins;
effective date of this AD: Submit the report AES–200. loss of the pins will result in the aft
within 60 days after the effective date of this mount engine link no longer being
AD. (l) Related Information secured to the aft engine mount,
(j) Post-Repair Provisions (1) Refer to Mandatory Continuing possibly resulting in damage to the
Airworthiness Information (MCAI) European airplane and injury to persons on the
(1) Accomplishment of corrective actions Airworthiness Directive 2015–0152, dated
required by this AD does not terminate the ground.
July 24, 2015, for related information. This
repetitive HFEC inspections required by MCAI may be found in the AD docket on the DATES: We must receive comments on
paragraph (g)(3) of this AD. this proposed AD by July 15, 2016.
Internet at http://www.regulations.gov by
(2) If all frame forks are replaced at the
searching for and locating Docket No. FAA– ADDRESSES: You may send comments,
same time on the aft LDCD of an airplane, the
2016–6894. using the procedures found in 14 CFR
next HFEC inspection required by paragraph
(g)(3) of this AD can be deferred up to 4,500 (2) For service information identified in 11.43 and 11.45, by any of the following
flight cycles after the frame fork replacement. this AD, contact Airbus SAS, Airworthiness methods:
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
Office—EAW, 1 Rond Point Maurice • Federal eRulemaking Portal: Go to
(k) Other FAA AD Provisions Bellonte, 31707 Blagnac Cedex, France;
http://www.regulations.gov. Follow the
The following provisions also apply to this telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-
instructions for submitting comments.
AD:
eas@airbus.com; Internet http:// • Fax: 202–493–2251.
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International www.airbus.com. You may view this service • Mail: U.S. Department of
Branch, ANM–116, Transport Airplane information at the FAA, Transport Airplane Transportation, Docket Operations, M–
Directorate, FAA, has the authority to Directorate, 1601 Lind Avenue SW., Renton, 30, West Building Ground Floor, Room
approve AMOCs for this AD, if requested WA. For information on the availability of W12–140, 1200 New Jersey Avenue SE.,
using the procedures found in 14 CFR 39.19. this material at the FAA, call 425–227–1221. Washington, DC 20590.
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• Hand Delivery: Deliver to Mail www.regulations.gov, including any 2015–NM–023–AD (80 FR 55798, September
address above between 9 a.m. and 5 personal information you provide. We 7, 2015)], retaining the requirements of EASA
p.m., Monday through Friday, except will also post a report summarizing each AD 2013–0050, which was superseded, and
Federal holidays. substantive verbal contact we receive requiring repetitive DET of all aft engine
For Airbus service information mount inner retainers and, depending on
about this proposed AD. findings, their replacement.
identified in this NPRM, contact Airbus, Since that [EASA] AD was issued, a
Airworthiness Office—EIAS, 1 Rond Discussion
production quality deficiency was identified
Point Maurice Bellonte, 31707 Blagnac The European Aviation Safety Agency by Airbus and UTAS (formerly Goodrich
Cedex, France; telephone: +33 5 61 93 (EASA), which is the Technical Agent Aerostructures, the engine mount retainer
36 96; fax: +33 5 61 93 44 51; email: for the Member States of the European manufacturer) on the delivery of the inner
account.airworth-eas@airbus.com; Union, has issued EASA Airworthiness retainer, Part Number (P/N) 238–0252–505,
Internet: http://www.airbus.com. Directive 2016–0010R1, dated February installed in the three Link assemblies of the
For Goodrich service information 16, 2016 (referred to after this as the engine mount fitted on CFM56–5A/5B
identified in this NPRM, contact Mandatory Continuing Airworthiness engines. Airbus issued AOT A71N011–15
Goodrich Corporation, Aerostructures, and SB A320–71–1070 providing a list of
Information, or ‘‘the MCAI’’), to correct affected parts and applicable corrective
850 Lagoon Drive, Chula Vista, CA an unsafe condition for all Airbus actions.
91910–2098; telephone: 619–691–2719; Model A318–111, and –112 airplanes, Consequently, EASA issued [a new] AD
email: jan.lewis@goodrich.com; Internet: Model A319–111, –112, –113, –114, and * * *, retaining the requirements of EASA
http://www.goodrich.com/TechPubs. –115 airplanes, Model A320–211, –212, AD 2015–0021, which was superseded, and
You may view this referenced service and –214 airplanes, and Model A321– in addition requiring the identification and
information at the FAA, Transport 111, –112, –211, –212, and –213 replacement of all non-conforming aft engine
Airplane Directorate, 1601 Lind Avenue airplanes. The MCAI states: mount inner retainers.
SW., Renton, WA. For information on Since that [new EASA] AD was issued,
the availability of this material at the During in-service inspections, several aft AOT A71N011–15 was revised, removing
engine mount inner retainers, fitted on errors and reducing the list of affected parts.
FAA, call 425–227–1221.
aeroplanes equipped with CFM56–5A/5B For the reason described above, this
Examining the AD Docket engines, have been found broken. The results [EASA] AD is revised, adding reference to the
of the initial investigations highlighted that revised AOT, and removing [EASA] AD
You may examine the AD docket on two different types of surface finish had been appendixes, which content is included in the
the Internet at http:// applied (respectively bright and dull material referenced Airbus documentation.
www.regulations.gov by searching for finishes), and that dull finish affects the This [EASA] AD is still considered to be
and locating Docket No. FAA–2016– strength of the retainer with regard to fatigue an interim action, pending development and
6896; or in person at the Docket properties of the part. The pins which attach availability of a final solution.
Management Facility between 9 a.m. the engine link to the aft mount are secured
by two nuts, which do not have a self-locking This proposed AD would require an
and 5 p.m., Monday through Friday,
feature; this function is provided by the inspection for, and replacement of, all
except Federal holidays. The AD docket
contains this proposed AD, the retainer brackets. In case of failure of the non-conforming aft engine mount
regulatory evaluation, any comments
retainer bracket, the locking feature of the retainers. You may examine the MCAI
nuts of the inner and outer pins is lost; as a in the AD docket on the Internet at
received, and other information. The result, these nuts could subsequently become
street address for the Docket Operations http://www.regulations.gov by searching
loose. for and locating Docket No. FAA–2016–
office (telephone: 800–647–5527) is in In case of full loss of the nuts, there is the
the ADDRESSES section. Comments will 6896.
potential to also lose the pins, in which case
be available in the AD docket shortly the aft mount link will no longer be secured Related Service Information Under 1
after receipt. to the aft engine mount. The same locking CFR Part 51
FOR FURTHER INFORMATION CONTACT: feature is used for the three link assemblies
of the aft mount. We reviewed the following service
Sanjay Ralhan, Aerospace Engineer, This condition, if not detected and information. This service information
International Branch, ANM–116, corrected, could lead to in-flight loss of an aft describes procedures for replacement of
Transport Airplane Directorate, FAA, mount link, possibly resulting in damage to all non-conforming aft engine mount
1601 Lind Avenue SW., Renton, WA the aeroplane and/or injury to persons on the retainers.
98057–3356; telephone: 425–227–1405; ground. • Airbus Service Bulletin A320–71–
fax: 425–227–1149. To address this potential unsafe condition, 1070, dated November 23, 2015. This
SUPPLEMENTARY INFORMATION: EASA issued AD 2013–0050 [http:// service information also describes
ad.easa.europa.eu/blob/easa_ad_2013_0050_
Comments Invited superseded.pdf/AD_2013–0050_1] [which
procedures for an inspection for non-
corresponds to FAA AD 2014–14–06, conforming aft engine mount retainers.
We invite you to send any written
Amendment 39–17901 (79 FR 42655, July 23, • Airbus Alert Operators
relevant data, views, or arguments about 2014)] to require a detailed inspection (DET) Transmission (AOT) A71N011–15,
this proposed AD. Send your comments of the aft engine mount inner retainers and Revision 01, dated February 1, 2016.
to an address listed under the the replacement of all retainers with dull • Goodrich Service Bulletin
ADDRESSES section. Include ‘‘Docket No. finish with retainers having a bright finish. RA32071–165, dated October 9, 2015.
FAA–2016–6896; Directorate Identifier Since that [EASA] AD was issued, inspection This service information is reasonably
2016–NM–016–AD’’ at the beginning of results showed that the main cause of crack available because the interested parties
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
your comments. We specifically invite initiation remains the vibration dynamic have access to it through their normal
comments on the overall regulatory, effect that affects both retainers, either with course of business or by the means
economic, environmental, and energy ‘‘dull’’ or ‘‘bright’’ surface finishes. The non-
conforming ‘‘dull’’ surface’s pitting is an
identified in the ADDRESSES section.
aspects of this proposed AD. We will aggravating factor. Consequently, EASA
consider all comments received by the FAA’s Determination and Requirements
issued AD 2015–0021 [http:// of This Proposed AD
closing date and may amend this ad.easa.europa.eu/blob/EASA_AD_2015_
proposed AD based on those comments. 0021_superseded.pdf/AD_2015–0021_1] This product has been approved by
We will post all comments we [which corresponds to FAA NPRM Docket the aviation authority of another
receive, without change, to http:// No. FAA–2015–3632; Directorate Identifier country, and is approved for operation
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![Federal Register / Vol. 81, No. 104 / Tuesday, May 31, 2016 / Proposed Rules 34289
in the United States. Pursuant to our AD because we evaluated all pertinent Costs of Compliance
bilateral agreement with the State of information and determined an unsafe
Design Authority, we have been notified condition exists and is likely to exist or We estimate that this proposed AD
of the unsafe condition described in the develop on other products of these same affects 959 airplanes of U.S. registry.
MCAI and service information type designs. We estimate the following costs to
referenced above. We are proposing this comply with this proposed AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Inspection ............................. 4 work-hours × $85 per hour = $340 .................................. $0 $340 Up to $326,060.
We estimate the following costs to do be required based on the results of the determining the number of airplanes
any necessary replacements that would proposed inspection. We have no way of that might need these replacements:
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Replacement ................................... Up to 36 work-hours × $85 per hour = $3,060 ..................................... $10,000 Up to $13,060.
Authority for This Rulemaking 3. Will not affect intrastate aviation in (1) Airbus Model A318–111 and –112
Alaska; and airplanes.
Title 49 of the United States Code (2) Airbus Model A319–111, –112, –113,
specifies the FAA’s authority to issue 4. Will not have a significant
–114, and –115 airplanes.
rules on aviation safety. Subtitle I, economic impact, positive or negative, (3) Airbus Model A320–211, –212, and
section 106, describes the authority of on a substantial number of small entities –214 airplanes.
the FAA Administrator. ‘‘Subtitle VII: under the criteria of the Regulatory (4) Airbus Model A321–111, –112, –211,
Aviation Programs,’’ describes in more Flexibility Act. –212, and –213 airplanes.
detail the scope of the Agency’s List of Subjects in 14 CFR Part 39 (d) Subject
authority. Air Transport Association (ATA) of
We are issuing this rulemaking under Air transportation, Aircraft, Aviation
America Code 71, Powerplant.
the authority described in ‘‘Subtitle VII, safety, Incorporation by reference,
Part A, Subpart III, Section 44701: Safety. (e) Reason
General requirements.’’ Under that The Proposed Amendment This AD was prompted by a report of a
section, Congress charges the FAA with production quality deficiency on the inner
Accordingly, under the authority retainer installed on link assemblies of the
promoting safe flight of civil aircraft in engine mount, which could result in failure
delegated to me by the Administrator,
air commerce by prescribing regulations of the retainer. We are issuing this AD to
the FAA proposes to amend 14 CFR part
for practices, methods, and procedures detect and correct non-conforming retainers
39 as follows:
the Administrator finds necessary for of the aft engine mount. This condition could
safety in air commerce. This regulation PART 39—AIRWORTHINESS result in loss of the locking feature of the
is within the scope of that authority nuts of the inner and outer pins; loss of the
DIRECTIVES pins will result in the aft mount engine link
because it addresses an unsafe condition
that is likely to exist or develop on no longer being secured to the aft engine
■ 1. The authority citation for part 39 mount, possibly resulting in damage to the
products identified in this rulemaking continues to read as follows: airplane and injury to persons on the ground.
action. Authority: 49 U.S.C. 106(g), 40113, 44701. (f) Compliance
Regulatory Findings
§ 39.13 [Amended] Comply with this AD within the
We determined that this proposed AD ■ 2. The FAA amends § 39.13 by adding compliance times specified, unless already
would not have federalism implications done.
the following new airworthiness
under Executive Order 13132. This directive (AD): (g) Inspection and Replacement
proposed AD would not have a
Airbus: Docket No. FAA–2016–6896; Within 2 months after the effective date of
substantial direct effect on the States, on this AD, do an inspection to determine the
Directorate Identifier 2016–NM–016–AD.
the relationship between the national part number of each engine mount inner
Government and the States, or on the (a) Comments Due Date retainer; and within 2 months after the
distribution of power and effective date of this AD, replace each part
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
We must receive comments by July 15,
responsibilities among the various 2016. that meets any of the criteria specified in
levels of government. paragraph (g)(1), (g)(2), or (g)(3) of this AD.
(b) Affected ADs Do the inspection in accordance with the
For the reasons discussed above, I
certify this proposed regulation: None. service information specified in paragraph
(h)(1) of this AD. Do the replacement in
1. Is not a ‘‘significant regulatory (c) Applicability accordance with the service information
action’’ under Executive Order 12866; This AD applies to the Airbus airplanes specified in paragraph (h)(1), (h)(2), or (h)(3)
2. Is not a ‘‘significant rule’’ under the identified in paragraphs (c)(1) through (c)(4) of this AD. A review of airplane maintenance
DOT Regulatory Policies and Procedures of this AD, certificated in any category, all records is acceptable in lieu of the inspection
(44 FR 11034, February 26, 1979); manufacturer serial numbers. required by this paragraph, if the part
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![34290 Federal Register / Vol. 81, No. 104 / Tuesday, May 31, 2016 / Proposed Rules
number of the engine mount inner retainer using the procedures found in 14 CFR 39.19. Issued in Renton, Washington, on May 20,
can be conclusively determined from that In accordance with 14 CFR 39.19, send your 2016.
review. request to your principal inspector or local Victor Wicklund,
(1) An aft engine mount having a serial Flight Standards District Office, as Acting Manager, Transport Airplane
number listed in table 1 of Airbus Alert appropriate. If sending information directly Directorate, Aircraft Certification Service.
Operators Transmission (AOT) A71N011–15, to the International Branch, send it to ATTN:
Rev 01, dated February 1, 2016. [FR Doc. 2016–12593 Filed 5–27–16; 8:45 am]
Sanjay Ralhan, Aerospace Engineer,
(2) An engine mount inner retainer International Branch, ANM–116, Transport BILLING CODE 4910–13–P
installed on an airplane between the first Airplane Directorate, FAA, 1601 Lind
flight of the airplane or March 1, 2015 Avenue SW., Renton, WA 98057–3356;
(whichever occurs later), and the effective telephone: 425–227–1405; fax: 425–227– DEPARTMENT OF HOUSING AND
date of this AD, and that can be identified by 1149. Information may be emailed to: 9- URBAN DEVELOPMENT
a purchase order (PO) listed in table 2 of ANM-116-AMOC-REQUESTS@faa.gov.
Airbus AOT A71N011–15, Rev 01, dated Before using any approved AMOC, notify 24 CFR Part 1000
February 1, 2016. your appropriate principal inspector, or
(3) An engine mount inner retainer lacking a principal inspector, the manager of [Docket No. FR–5650–P–12]
installed on an airplane between the first the local flight standards district office/
flight of the airplane or March 1, 2015 RIN 2577–AC90
certificate holding district office. The AMOC
(whichever occurs later), and the effective
approval letter must specifically reference Native American Housing Assistance
date of this AD, and that cannot be identified
this AD. and Self-Determination Act; Revisions
by a PO.
(2) Contacting the Manufacturer: For any
to the Indian Housing Block Grant
(h) Service Information for Actions Required requirement in this AD to obtain corrective
by Paragraph (g) of This AD actions from a manufacturer, the action must
Program Formula
Accomplish the replacement required by be accomplished using a method approved AGENCY: Office of the Assistant
paragraph (g) of this AD in accordance with by the Manager, International Branch, ANM– Secretary for Public and Indian
the service information specified in 116, Transport Airplane Directorate, FAA; or Housing, HUD.
paragraph (h)(1), (h)(2), or (h)(3) of this AD. the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design ACTION: Proposed rule.
(1) The Accomplishment Instructions of
Airbus Service Bulletin A320–71–1070, Organization Approval (DOA). If approved by
SUMMARY: This proposed rule would
dated November 23, 2015. the DOA, the approval must include the
DOA-authorized signature. revise the Indian Housing Block Grant
(2) Paragraph 4.2.2, ‘‘Requirements,’’ of
Airbus AOT A71N011–15, Revision 01, dated (3) Required for Compliance (RC): If any (IHBG) Program allocation formula
February 1, 2016. service information contains procedures or authorized by section 302 of the Native
(3) The Accomplishment Instructions of tests that are identified as RC, those American Housing Assistance and Self-
Goodrich Service Bulletin RA32071–165, procedures and tests must be done to comply Determination Act of 1996, as amended
dated October 9, 2015. with this AD; any procedures or tests that are (NAHASDA). Through the IHBG
not identified as RC are recommended. Those Program, HUD provides federal housing
(i) Credit for Previous Actions procedures and tests that are not identified assistance for Indian tribes in a manner
This paragraph provides credit for the as RC may be deviated from using accepted that recognizes the right of Indian self-
applicable actions required by paragraph (g) methods in accordance with the operator’s
of this AD, if those actions were performed determination and tribal self-
maintenance or inspection program without
before the effective date of this AD using obtaining approval of an AMOC, provided
government. HUD negotiated the
Airbus AOT A71N011–15, Revision 01, dated the procedures and tests identified as RC can proposed rule with active tribal
February 1, 2016, which is not incorporated be done and the airplane can be put back in participation and using the procedures
by reference in this AD. an airworthy condition. Any substitutions or of the Negotiated Rulemaking Act of
(j) Parts Installation Prohibition changes to procedures or tests identified as 1990. The proposed regulatory changes
RC require approval of an AMOC. reflect the consensus decisions reached
As of the effective date of this AD, no
person may install any part that meets any (m) Related Information by HUD and the tribal representatives
of the criteria specified in paragraph (j)(1), on ways to improve and clarify the
(1) Refer to Mandatory Continuing
(j)(2), (j)(3) of this AD on any airplane. current regulations governing the IHBG
Airworthiness Information (MCAI) EASA AD
(1) An aft engine mount having a serial 2016–0010R1, dated February 16, 2016, for Program formula.
number listed in table 1 of Airbus AOT related information. This MCAI may be DATES: Comment Due Date: August 1,
A71N011–15, Rev 01, dated February 1, found in the AD docket on the Internet at 2016.
2016. http://www.regulations.gov by searching for
(2) An engine mount inner retainer ADDRESSES: Interested persons are
and locating Docket No. FAA–2016–6896.
delivered through a PO listed in table 2 of invited to submit comments regarding
(2) For Airbus service information
Airbus AOT A71N011–15, Rev 01, dated
identified in this AD, contact Airbus,
this proposed rule to the Regulations
February 1, 2016. Division, Office of General Counsel,
Airworthiness Office—EIAS, 1 Rond Point
(3) An engine mount inner retainer Department of Housing and Urban
Maurice Bellonte, 31707 Blagnac Cedex,
delivered through an unidentified PO. Development, 451 7th Street SW., Room
France; telephone: +33 5 61 93 36 96; fax:
(k) Special Flight Permits +33 5 61 93 44 51; email: account.airworth- 10276, Washington, DC 20410–0500.
Special flight permits, as described in eas@airbus.com; Internet: http:// Communications must refer to the above
Section 21.197 and Section 21.199 of the www.airbus.com. For Goodrich service docket number and title. There are two
Federal Aviation Regulations (14 CFR 21.197 information identified in this AD, contact methods for submitting public
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
and 21.199), are not allowed. Goodrich Corporation, Aerostructures, 850 comments. All submissions must refer
Lagoon Drive, Chula Vista, CA 91910–2098;
(l) Other FAA AD Provisions to the above docket number and title.
telephone: 619–691–2719; email: jan.lewis@
1. Submission of Comments by Mail.
The following provisions also apply to this goodrich.com; Internet: http://
www.goodrich.com/TechPubs. You may view
Comments may be submitted by mail to
AD:
(1) Alternative Methods of Compliance this service information at the FAA, the Regulations Division, Office of
(AMOCs): The Manager, International Transport Airplane Directorate, 1601 Lind General Counsel, Department of
Branch, ANM–116, Transport Airplane Avenue SW., Renton, WA. For information Housing and Urban Development, 451
Directorate, FAA, has the authority to on the availability of this material at the 7th Street SW., Room 10276,
approve AMOCs for this AD, if requested FAA, call 425–227–1221. Washington, DC 20410–0500.
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Document Created: 2016-05-28 03:57:42
Document Modified: 2016-05-28 03:57:42
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by July 15, 2016. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1405; fax: 425-227-1149. | |
| FR Citation | 81 FR 34287 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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