Airworthiness Directives; Airbus Airplanes
Federal Register, Volume 81 Issue 149 (Wednesday, August 3, 2016)
Federal Register Volume 81, Number 149 (Wednesday, August 3, 2016)
Proposed Rules
Pages 51142-51144
From the Federal Register Online via the Government Publishing Office www.gpo.gov
FR Doc No: 2016-18262
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Docket No. FAA-2016-8182; Directorate Identifier 2016-NM-069-AD
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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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 reports of cracks on the 3 o'clock and 9 o'clock pivot fittings of a CFM56 engine's thrust reverser (T/R). This proposed AD would require repetitive inspections for cracking and corrosion of the 3 o'clock and 9 o'clock pivot fittings of a CFM56 engine's T/R, and corrective actions if necessary. We are proposing this AD to detect and correct such cracking and corrosion, which could lead to T/R malfunction and, in a case of rejected takeoff at V1 on a wet runway, a consequent runway excursion, possibly resulting in damage to the airplane and injury to occupants.
DATES: We must receive comments on this proposed AD by September 19, 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.
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 account.airworth-eas@airbus.com; Internet http://www.airbus.com.
For Goodrich Aerostructures service information identified in this NPRM, contact Goodrich Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098; telephone 619-691-2719; email jan.lewis@goodrich.com; 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-
8182; 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-2016-8182; Directorate Identifier 2016-NM-069-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 2016-0076, dated April 18, 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, v211, -212, and -213 airplanes. The MCAI states:
Several operators reported finding cracks, during an unscheduled inspection, on the 3 o'clock and 9 o'clock pivot fittings of a CFM56 engine's thrust reverser (T/R). Investigation results revealed that these cracks were caused by a combination of stress and fatigue effects. Further analysis determined that only aeroplanes fitted with
Page 51143
CFM56-5A or CFM56-5B series engines could be affected by this issue.
This condition, if not detected and corrected, could lead to T/R malfunction and, in a case of rejected take off at V1 on a wet runway, a consequent runway excursion, possibly resulting in damage to the aeroplane and injury to occupants.
For the reasons described above, EASA issued AD 2016-0068, requiring repetitive inspections for cracks and corrosion of the T/R pivot fittings at the 3 o'clock and 9 o'clock positions and, depending on findings, accomplishment of applicable corrective action(s).
Since that EASA AD was issued, it was determined that the list of part numbers (P/N) of affected T/R pivot fitting, as identified in that EASA AD, was incomplete.
For the reason stated above, this EASA AD retains the requirements of EASA AD 2016-0068, which is superseded, but expands the list of affected fitting P/Ns.
Corrective actions include repair of cracking and corrosion.
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-
8182.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-70-1003, Revision 01, dated December 18, 2015. This service information describes procedures for doing inspections for cracking and corrosion of the 3 o'clock and 9 o'clock pivot fittings of a CFM56 engine's T/R.
Goodrich Aerostructures has issued Service Bulletin RA32078-137, Rev. 3, dated March 14, 2016. This service information describes procedures for doing inspections for cracking and corrosion of the 3 o'clock and 9 o'clock pivot fittings of a CFM56 engine's T/R, and repair of corrosion.
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 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 400 airplanes of U.S. registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Inspection..................... 4 work-hours x $85 per $0 $340 per $136,000 per
hour = $340 per inspection cycle. inspection
inspection cycle. cycle.
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We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.
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
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2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD):
Airbus: Docket No. FAA-2016-8182; Directorate Identifier 2016-NM-
069-AD.
(a) Comments Due Date
We must receive comments by September 19, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes, certificated in any category, identified in paragraphs (c)(1) through (c)(4) of this AD, 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.
Page 51144
(d) Subject
Air Transport Association (ATA) of America Code 78, Engine exhaust.
(e) Reason
This AD was prompted by reports of cracks on the 3 o'clock and 9 o'clock pivot fittings of a CFM56 engine's thrust reverser (T/R). We are issuing this AD to detect and correct such cracking and corrosion, which could lead to T/R malfunction and, in a case of rejected takeoff at V1 on a wet runway, a consequent runway excursion, possibly resulting in damage to the airplane and injury to occupants.
(f) Compliance
Comply with this AD within the compliance times specified, unless already done.
(g) Inspections and Corrective Actions
At the applicable compliance time specified in paragraph (h) of this AD: Do a high frequency eddy current (HFEC) inspection for cracking and corrosion of each T/R pivot fitting specified in paragraphs (g)(1) and (g)(2) of this AD, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-70-1003, Revision 01, dated December 18, 2015; and Goodrich Aerostructures Service Bulletin RA32078-137, Rev. 3, dated March 14, 2016; as applicable; except as required by paragraph (i) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection of the T/R pivot fittings thereafter at intervals not to exceed 60 months or 12,000 flight cycles, whichever occurs first.
(1) The 3 o'clock position T/R pivot fittings having part numbers (P/N) that are provided in paragraphs (g)(1)(i) through (g)(1)(iv) of this AD.
(i) P/N 321-200-850-6.
(ii) P/N 321-200-851-6.
(iii) P/N 321-200-852-6.
(iv) P/N 321-200-853-6.
(2) The 9 o'clock position T/R pivot fittings having P/Ns that are provided in paragraphs (g)(2)(i) through (g)(2)(iv) of this AD.
(i) P/N 321-200-800-6.
(ii) P/N 321-200-801-6.
(iii) P/N 321-200-802-6.
(iv) P/N 321-200-803-6.
(h) Compliance Times
At the later of the times specified in paragraphs (h)(1) and (h)(2) of this AD, do the initial inspection specified in paragraph (g) of this AD. If maintenance records cannot conclusively determine the T/R flight cycles accumulated since first installation, or the time since new, do the initial inspection required by paragraph (g) of this AD at the compliance time specified in paragraph (h)(2) of this AD.
(1) Before exceeding 10 years or 24,000 total flight cycles accumulated by the T/R, whichever occurs first since first installation on an airplane.
(2) Within 36 months or 7,200 flight cycles, whichever occurs first after the effective date of this AD.
(i) Exceptions to Service Information Specification
(1) If any crack is found during any inspection required by this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
(2) If any corrosion is found during any inspection required by this AD and Goodrich Aerostructures Service Bulletin RA32078-137, Rev. 3, dated March 14, 2016, specifies obtaining a damage disposition from Goodrich Aerostructures: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA.
(j) Parts Installation Limitation
As of the effective date of this AD, no person may install on any airplane a T/R pivot fitting having a part number specified in paragraph (g)(1) or (g)(2) of this AD, unless it is determined, prior to installation, that the T/R pivot fitting has accumulated less than 10 years and fewer than 24,000 total flight cycles since its first installation on an airplane, or less than 60 months and fewer than 12,000 flight cycles after having passed an inspection in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-70-1003, Revision 01, dated December 18, 2015; and Goodrich Aerostructures Service Bulletin RA32078-137, Rev. 3, dated March 14, 2016.
(k) Credit for Previous Actions
(1) This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-70-
1003, dated May 7, 2014.
(2) This paragraph provides credit for actions specified in paragraph (j) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraph (k)(2)(i), or (k)(2)(ii), or (k)(2)(iii) of this AD.
(i) Airbus Service Bulletin A320-70-1003, dated May 7, 2014; and Goodrich Aerostructures Service Bulletin RA32078-137, dated April 29, 2014.
(ii) Airbus Service Bulletin A320-70-1003, dated May 7, 2014; and Goodrich Aerostructures Service Bulletin RA32078-137, Rev. 1, dated January 26, 2015.
(iii) Airbus Service Bulletin A320-70-1003, dated May 7, 2014; and Goodrich Aerostructures Service Bulletin RA32078-137, Rev. 2, dated December 2, 2015.
(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: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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 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 (i) 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.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016-0076, dated April 18, 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-2016-8182.
(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 account.airworth-eas@airbus.com; Internet http://www.airbus.com.
(3) For Goodrich Aerostructures service information identified in this AD, contact Goodrich Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098; telephone 619-691-2719; email jan.lewis@goodrich.com; Internet http://www.goodrich.com/TechPubs.
(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.
Issued in Renton, Washington, on July 25, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
FR Doc. 2016-18262 Filed 8-2-16; 8:45 am
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