82 FR 23160 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 97 (May 22, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 97 (May 22, 2017)
| Page Range | 23160-23163 | |
| FR Document | 2017-10138 |
[Federal Register Volume 82, Number 97 (Monday, May 22, 2017)] [Proposed Rules] [Pages 23160-23163] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-10138] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0478; Directorate Identifier 2016-NM-174-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 certain Airbus Model A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233, airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This proposed AD was prompted by a report of cracks on frame forks and outer skin on the forward and aft cargo compartment doors. This proposed AD would require repetitive inspections of the frame forks, and corrective actions if necessary. This proposed AD would also include optional modifications that constitute terminating action. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by July 6, 2017. 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 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. 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-2017- 0478; 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-2017-0478; Directorate Identifier 2016-NM-174-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 [[Page 23161]] 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 AD 2016-0187, dated September 19, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233, airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. The MCAI states: During full scale fatigue test, cracks have been found on frame forks and outer skin on forward and aft cargo doors. To improve the fatigue behaviour of the frame forks, Airbus introduced modification (mod) 22948 in production, and issued inspection Service Bulletin (SB) A320-52-1032 and modification SB A320-52-1042, both recommended. Since those actions were taken, further improved cargo compartment doors have been introduced in production through Airbus mod 26213, on aeroplanes having MSN 0759 and up. This modification, which is not available for in-service retrofit, also includes provisions that exclude installation of pre-mod 26213 aft and forward compartment cargo doors on an aeroplane. In the frame of the Widespread Fatigue Damage (WFD) study, it has been determined that repetitive inspections are necessary for aft and forward cargo compartment doors on aeroplanes that do not (or no longer) embody mod 22948 (or SB A320-52-1042), and those that do not embody mod 26213. Failure to detect cracks would reduce the cargo door structural integrity. This condition, if not detected and corrected, could lead to cargo door failure, possibly resulting in decompression of the aeroplane and injury to occupants. To address this unsafe condition, Airbus issued SB A320-52-1171 to provide inspection instructions. This SB was later revised to correct the list of affected cargo doors. Airbus also issued SB A320-52-1170, introducing a door modification which constitutes terminating action for the repetitive special detailed inspection (SDI). For the reason described above, this [EASA] AD requires accomplishment of repetitive SDI by rototest of all frame forks in beam 4 area to detect cracks, and, depending on findings, accomplishment of applicable corrective action(s) [repair or replacement]. This AD also provides an optional [modification that constitutes] terminating action for the repetitive SDI required by this [EASA] AD. One of the optional modifications includes related investigative and corrective actions. The related investigative action is a high frequency eddy current (HFEC) rotating probe inspection for cracks, and the corrective action is a 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-2017-0478. Related Service Information Under 1 CFR Part 51 We reviewed the following Airbus service information. Airbus Service Bulletin A320-52-1171, Revision 01, dated September 5, 2016, describes procedures for repetitive special detailed inspections of all frame forks in the beam 4 area of any affected door, and corrective actions. Airbus Service Bulletin A320-52-1042, Revision 2, dated January 14, 1997, describes procedures for modification of all affected forward and aft cargo compartment doors of an airplane. Airbus Service Bulletin A320-52-1170, dated September 5, 2016, describes modification of all affected forward and aft cargo compartment doors of an airplane, including related investigative and corrective actions. 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. Difference Between This Proposed AD and the MCAI or Service Information Note 2 of the MCAI specifies to refer to Airbus A318/A319/A320/A321 Airworthiness Limitations Section (ALS) Part 1--Safe Life Airworthiness Limitation Items, Section 1, Chapter 5.2 (traceability). However, that document refers to an Airbus document to which we do not have access, and therefore we have not included a reference to Airbus A318/A319/ A320/A321 ALS Part 1--Safe Life Airworthiness Limitation Items, Section 1, Chapter 5.2 (traceability) in this proposed AD. Costs of Compliance We estimate that this proposed AD affects 88 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Special detailed inspection........... 25 work-hours x $85 per $0 $2,125 $187,000 hour = $2,125. ---------------------------------------------------------------------------------------------------------------- Optional Actions ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Modification......................... 24 work-hours x $85 per Up to $240............. Up to $2,280. hour = $2,040. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition repairs and replacements 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. [[Page 23162]] 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-2017-0478; Directorate Identifier 2016-NM- 174-AD. (a) Comments Due Date We must receive comments by July 6, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A319-111, -112, -113, -114, - 115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, - 231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes, certificated in any category, manufacturer serial numbers through 0758 inclusive. (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Reason This AD was prompted by a report of cracks on the frame forks and outer skin on the forward and aft cargo compartment doors. We are issuing this AD to detect and correct cracks on the frame forks and outer skin on the forward and aft cargo compartment doors, which could lead to reduced structural integrity and failure of the cargo compartment door, possible decompression of the airplane, and injury to occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definition of Affected Door For the purpose of this AD, an ``affected door'' is a forward or aft cargo compartment door, having any part number listed in table 1 to paragraph (g) of this AD, except a cargo compartment door on which Airbus Service Bulletin A320-52-1042 or Airbus Service Bulletin A320-52-1170 is embodied. Table 1 to Paragraph (g) of This AD--Affected Part Numbers ------------------------------------------------------------------------ Aft cargo Forward cargo compartment door part Nos. compartment door part Nos. ------------------------------------------------------------------------ D52371000000......................................... D52371900000 D52371000002......................................... D52371900002 D52371000004......................................... D52371900004 D52371000006......................................... D52371900008 D52371000008......................................... D52371900010 D52371000010......................................... D52371900012 D52371000012......................................... D52371900014 D52371000014......................................... D52371900016 D52371000016......................................... D52371900018 D52371000018......................................... D52371900022 D52371000022......................................... ................. ------------------------------------------------------------------------ (h) Repetitive Special Detailed Inspection of Frame Forks At the latest of the compliance times listed in paragraphs (h)(1) through (h)(4) of this AD: Do a special detailed inspection of all frame forks in the beam 4 area of any affected door as defined in paragraph (g) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1171, Revision 01, dated September 5, 2016 (``SB A320-52-1171 R01''), except as specified in paragraphs (k) and (l) of this AD. Repeat the inspection thereafter at intervals not to exceed 3,000 flight cycles. A review of the airplane delivery or maintenance records is acceptable to identify any affected door installed on the airplane, provided that the cargo compartment door part number can be conclusively determined from that review. (1) Before exceeding 37,500 flight cycles since first installation of the door on an airplane. (2) Within 900 flight cycles after the effective date of this AD, without exceeding 41,950 flight cycles since first installation of the door on an airplane. (3) Within 50 flight cycles after the effective date of this AD, for a door having reached or exceeded 41,900 flight cycles since first installation on an airplane. (4) Within 3,000 flight cycles since the last inspection of the door as specified in Airbus Service Bulletin A320-52-1032. (i) Corrective Actions If any crack is found during any inspection required by paragraph (h) of this AD, before further flight, do all applicable corrective actions in accordance with the Accomplishment Instructions of SB A320-52-1171 R01, except as specified in paragraphs (k) and (l) of this AD. Accomplishment of applicable corrective actions does not constitute terminating action for the repetitive inspections. (j) Optional Terminating Action (1) Modification of all affected doors of an airplane in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1042, Revision 2, dated January 14, 1997, constitutes terminating action for the repetitive inspections specified in paragraph (h) of this AD for that airplane, provided that, after modification, no affected door is re-installed on that airplane. (2) Modification of all affected doors of an airplane including accomplishment of all applicable related investigative and corrective actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1170, dated September 5, 2016, except as specified in paragraphs (k) and (l) of this AD, constitutes terminating action for the repetitive inspections specified in paragraph (h) of this AD for that airplane, provided that, after modification, no affected door is re-installed on that airplane. (3) Modification of all affected doors on an airplane, in case of finding damaged frame forks, as specified in an Airbus Repair Design Approval Sheet (RDAS), and done in accordance with 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); constitutes terminating action for the repetitive inspection specified in paragraph (h) of this AD for that airplane, provided that, after modification, no affected door is re-installed on that airplane. (k) Exception to Service Information Where SB A320-52-1171 R01 specifies to contact Airbus for appropriate action, and specifies that action as ``RC'' (Required for Compliance): Before further flight, accomplish corrective actions in accordance [[Page 23163]] with the procedures specified in paragraph (o)(2) of this AD. (l) No Reporting Requirement Although SB A320-52-1171 R01 specifies to submit certain information to the manufacturer, and specifies that action as ``RC'' (Required for Compliance), this AD does not include that requirement. (m) Credit for Previous Actions This paragraph provides credit for the actions required by paragraphs (h) and (i) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-52-1171, dated October 29, 2015, provided that it can be conclusively determined that any part number D52371000018 was also inspected as specified in paragraph (h) of this AD. (n) Parts Installation Limitation As of the effective date of this AD, no person may install, on any airplane, an affected door specified in paragraph (g) of this AD, unless it has been inspected in accordance with the requirements of paragraph (h) of this AD and all applicable corrective actions have been done in accordance with paragraph (i) of this AD. (o) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, 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 manager of the International Branch, send it to the attention of the person identified in paragraph (p)(2) of this AD. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or 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 specified in paragraphs (k) and (l) 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. (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016-0187, dated September 19, 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-2017-0478. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone: 425-227-1405; fax: 425-227-1149. (3) For service information identified in this AD, contact Airbus, Airworthiness--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this 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 12, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-10138 Filed 5-19-17; 8:45 am] BILLING CODE 4910-13-P
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(f) Compliance Transport Airplane Directorate, FAA, 1601 30, West Building Ground Floor, Room
Comply with this AD within the Lind Avenue SW., Renton, WA 98057–3356; W12–140, 1200 New Jersey Avenue SE.,
compliance times specified, unless already telephone 425–227–1112; fax 425–227–1149. Washington, DC 20590.
(3) For service information identified in
done.
this AD, contact Saab AB, Saab Aeronautics,
• Hand Delivery: Deliver to Mail
(g) Replacement SE–581 88, Linköping, Sweden; telephone address above between 9 a.m. and 5
+46 13 18 5591; fax +46 13 18 4874; email p.m., Monday through Friday, except
Within 6 months after the effective date of
this AD: Replace any circuit breaker having saab340techsupport@saabgroup.com; Federal holidays.
part number (P/N) MS3320–10 installed at Internet http://www.saabgroup.com. You For service information identified in
position 2LJ (L25) and position 4LJ (L26) may view this service information at the this NPRM, contact Airbus,
with a circuit breaker having P/N MS3320– FAA, Transport Airplane Directorate, 1601 Airworthiness Office—EIAS, 1 Rond
Lind Avenue SW., Renton, WA. For
7–5, in accordance with the Accomplishment Point Maurice Bellonte, 31707 Blagnac
information on the availability of this
Instructions of Saab Service Bulletin 340–33– Cedex, France; telephone: +33 5 61 93
material at the FAA, call 425–227–1221.
058, Revision 01, dated October 21, 2016. 36 96; fax: +33 5 61 93 44 51; email:
Issued in Renton, Washington, on May 12, account.airworth-eas@airbus.com;
(h) Parts Installation Prohibition 2017.
As of the effective date of this AD, no
Internet: http://www.airbus.com. You
Michael Kaszycki,
person may install a circuit breaker P/N may view this referenced service
Acting Manager, Transport Airplane information at the FAA, Transport
MS3320–10 on any passenger reading light Directorate, Aircraft Certification Service.
system at position at 2LJ (L25) and position Airplane Directorate, 1601 Lind Avenue
4LJ (L26), on any airplane. [FR Doc. 2017–10139 Filed 5–19–17; 8:45 am] SW., Renton, WA. For information on
(i) Credit for Previous Actions
BILLING CODE 4910–13–P the availability of this material at the
FAA, call 425–227–1221.
This paragraph provides credit for the
actions required by paragraph (g) of this AD, DEPARTMENT OF TRANSPORTATION Examining the AD Docket
if those actions were performed before the
effective date of this AD using Saab Service
You may examine the AD docket on
Federal Aviation Administration
Bulletin 340–33–058, dated May 30, 2016. the Internet at http://
www.regulations.gov by searching for
(j) Other FAA AD Provisions 14 CFR Part 39
and locating Docket No. FAA–2017–
The following provisions also apply to this [Docket No. FAA–2017–0478; Directorate 0478; or in person at the Docket
AD: Identifier 2016–NM–174–AD] Management Facility between 9 a.m.
(1) Alternative Methods of Compliance and 5 p.m., Monday through Friday,
(AMOCs): The Manager, International RIN 2120–AA64
except Federal holidays. The AD docket
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to Airworthiness Directives; Airbus contains this proposed AD, the
approve AMOCs for this AD, if requested Airplanes regulatory evaluation, any comments
using the procedures found in 14 CFR 39.19. received, and other information. The
AGENCY: Federal Aviation
In accordance with 14 CFR 39.19, send your street address for the Docket Operations
Administration (FAA), DOT.
request to your principal inspector or local office (telephone: 800–647–5527) is in
Flight Standards District Office, as ACTION: Notice of proposed rulemaking the ADDRESSES section. Comments will
appropriate. If sending information directly (NPRM). be available in the AD docket shortly
to the manager of the International Branch, after receipt.
send it to the attention of the person SUMMARY: We propose to adopt a new
identified in paragraph (k)(2) of this AD. airworthiness directive (AD) for certain FOR FURTHER INFORMATION CONTACT:
Information may be emailed to: 9-ANM-116- Airbus Model A319 series airplanes; Sanjay Ralhan, Aerospace Engineer,
AMOC-REQUESTS@faa.gov. Before using Model A320–211, –212, –214, –231, International Branch, ANM–116,
any approved AMOC, notify your appropriate –232, and –233, airplanes; and Model Transport Airplane Directorate, FAA,
principal inspector, or lacking a principal A321–111, –112, –131, –211, –212, 1601 Lind Avenue SW., Renton, WA
inspector, the manager of the local flight –213, –231, and –232 airplanes. This 98057–3356; telephone: 425–227–1405;
standards district office/certificate holding proposed AD was prompted by a report fax: 425–227–1149.
district office.
(2) Contacting the Manufacturer: For any
of cracks on frame forks and outer skin SUPPLEMENTARY INFORMATION:
requirement in this AD to obtain corrective on the forward and aft cargo
compartment doors. This proposed AD Comments Invited
actions from a manufacturer, the action must
be accomplished using a method approved would require repetitive inspections of We invite you to send any written
by the Manager, International Branch, ANM– the frame forks, and corrective actions if relevant data, views, or arguments about
116, Transport Airplane Directorate, FAA; or necessary. This proposed AD would this proposed AD. Send your comments
the European Aviation Safety Agency also include optional modifications that to an address listed under the
(EASA); or Saab AB, Saab Aeronautics’ EASA constitute terminating action. We are ADDRESSES section. Include ‘‘Docket No.
Design Organization Approval (DOA). If proposing this AD to address the unsafe FAA–2017–0478; Directorate Identifier
approved by the DOA, the approval must
include the DOA-authorized signature.
condition on these products. 2016–NM–174–AD’’ at the beginning of
DATES: We must receive comments on your comments. We specifically invite
(k) Related Information this proposed AD by July 6, 2017. comments on the overall regulatory,
(1) Refer to Mandatory Continuing ADDRESSES: You may send comments, economic, environmental, and energy
Airworthiness Information (MCAI) EASA using the procedures found in 14 CFR aspects of this proposed AD. We will
nlaroche on DSK30NT082PROD with PROPOSALS
Airworthiness Directive 2016–0234, dated consider all comments received by the
11.43 and 11.45, by any of the following
November 24, 2016, for related information. closing date and may amend this
This MCAI may be found in the AD docket methods:
on the Internet at http://www.regulations.gov • Federal eRulemaking Portal: Go to proposed AD based on those comments.
by searching for and locating Docket No. http://www.regulations.gov. Follow the We will post all comments we
FAA–2017–0479. instructions for submitting comments. receive, without change, to http://
(2) For more information about this AD, • Fax: 202–493–2251. www.regulations.gov, including any
contact Shahram Daneshmandi, Aerospace • Mail: U.S. Department of personal information you provide. We
Engineer, International Branch, ANM–116, Transportation, Docket Operations, M– will also post a report summarizing each
VerDate Sep<11>2014 12:41 May 19, 2017 Jkt 241001 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 E:\FR\FM\22MYP1.SGM 22MYP1](https://thefederalregister.org/doc/82_FR_23257/page/1.svg)
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substantive verbal contact we receive To address this unsafe condition, Airbus forward and aft cargo compartment
about this proposed AD. issued SB A320–52–1171 to provide doors of an airplane, including related
inspection instructions. This SB was later investigative and corrective actions.
Discussion revised to correct the list of affected cargo
doors. Airbus also issued SB A320–52–1170,
This service information is reasonably
The European Aviation Safety Agency introducing a door modification which available because the interested parties
(EASA), which is the Technical Agent constitutes terminating action for the have access to it through their normal
for the Member States of the European repetitive special detailed inspection (SDI). course of business or by the means
Union, has issued EASA AD 2016–0187, For the reason described above, this identified in the ADDRESSES section.
[EASA] AD requires accomplishment of
dated September 19, 2016 (referred to FAA’s Determination and Requirements
repetitive SDI by rototest of all frame forks
after this as the Mandatory Continuing in beam 4 area to detect cracks, and, of This Proposed AD
Airworthiness Information, or ‘‘the depending on findings, accomplishment of
MCAI’’), to correct an unsafe condition applicable corrective action(s) [repair or
This product has been approved by
for certain Airbus Model A319 series replacement]. This AD also provides an the aviation authority of another
airplanes; Model A320–211, –212, –214, optional [modification that constitutes] country, and is approved for operation
–231, –232, and –233, airplanes; and terminating action for the repetitive SDI in the United States. Pursuant to our
Model A321–111, –112, –131, –211, required by this [EASA] AD. bilateral agreement with the State of
–212, –213, –231, and –232 airplanes. One of the optional modifications Design Authority, we have been notified
The MCAI states: includes related investigative and of the unsafe condition described in the
corrective actions. The related MCAI and service information
During full scale fatigue test, cracks have referenced above. We are proposing this
been found on frame forks and outer skin on investigative action is a high frequency
forward and aft cargo doors. eddy current (HFEC) rotating probe AD because we evaluated all pertinent
To improve the fatigue behaviour of the inspection for cracks, and the corrective information and determined an unsafe
frame forks, Airbus introduced modification action is a repair. You may examine the condition exists and is likely to exist or
(mod) 22948 in production, and issued MCAI in the AD docket on the Internet develop on other products of these same
inspection Service Bulletin (SB) A320–52– at http://www.regulations.gov by type designs.
1032 and modification SB A320–52–1042, searching for and locating Docket No.
both recommended. Difference Between This Proposed AD
FAA–2017–0478. and the MCAI or Service Information
Since those actions were taken, further
improved cargo compartment doors have Related Service Information Under 1 Note 2 of the MCAI specifies to refer
been introduced in production through CFR Part 51 to Airbus A318/A319/A320/A321
Airbus mod 26213, on aeroplanes having Airworthiness Limitations Section
MSN 0759 and up. This modification, which We reviewed the following Airbus
is not available for in-service retrofit, also service information. (ALS) Part 1—Safe Life Airworthiness
includes provisions that exclude installation • Airbus Service Bulletin A320–52– Limitation Items, Section 1, Chapter 5.2
of pre-mod 26213 aft and forward 1171, Revision 01, dated September 5, (traceability). However, that document
compartment cargo doors on an aeroplane. 2016, describes procedures for repetitive refers to an Airbus document to which
In the frame of the Widespread Fatigue special detailed inspections of all frame we do not have access, and therefore we
Damage (WFD) study, it has been determined forks in the beam 4 area of any affected have not included a reference to Airbus
that repetitive inspections are necessary for door, and corrective actions. A318/A319/A320/A321 ALS Part 1—
aft and forward cargo compartment doors on • Airbus Service Bulletin A320–52– Safe Life Airworthiness Limitation
aeroplanes that do not (or no longer) embody 1042, Revision 2, dated January 14, Items, Section 1, Chapter 5.2
mod 22948 (or SB A320–52–1042), and those 1997, describes procedures for (traceability) in this proposed AD.
that do not embody mod 26213. Failure to
detect cracks would reduce the cargo door
modification of all affected forward and
Costs of Compliance
structural integrity. aft cargo compartment doors of an
This condition, if not detected and airplane. We estimate that this proposed AD
corrected, could lead to cargo door failure, • Airbus Service Bulletin A320–52– affects 88 airplanes of U.S. registry.
possibly resulting in decompression of the 1170, dated September 5, 2016, We estimate the following costs to
aeroplane and injury to occupants. describes modification of all affected comply with this proposed AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Special detailed inspection ............................. 25 work-hours × $85 per hour = $2,125 ........ $0 $2,125 $187,000
OPTIONAL ACTIONS
Action Labor cost Parts cost Cost per product
Modification .................................... 24 work-hours × $85 per hour = Up to $240 .................................... Up to $2,280.
$2,040.
nlaroche on DSK30NT082PROD with PROPOSALS
We have received no definitive data Authority for This Rulemaking the FAA Administrator. ‘‘Subtitle VII:
that would enable us to provide cost Aviation Programs,’’ describes in more
estimates for the on-condition repairs Title 49 of the United States Code detail the scope of the Agency’s
and replacements specified in this specifies the FAA’s authority to issue authority.
proposed AD. rules on aviation safety. Subtitle I,
section 106, describes the authority of
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![23162 Federal Register / Vol. 82, No. 97 / Monday, May 22, 2017 / Proposed Rules
We are issuing this rulemaking under (b) Affected ADs the airplane delivery or maintenance records
the authority described in ‘‘Subtitle VII, None. is acceptable to identify any affected door
Part A, Subpart III, Section 44701: installed on the airplane, provided that the
(c) Applicability cargo compartment door part number can be
General requirements.’’ Under that conclusively determined from that review.
section, Congress charges the FAA with This AD applies to Airbus Model A319–
111, –112, –113, –114, –115, –131, –132, and (1) Before exceeding 37,500 flight cycles
promoting safe flight of civil aircraft in –133 airplanes; Model A320–211, –212, –214, since first installation of the door on an
air commerce by prescribing regulations –231, –232, and –233 airplanes; and Model airplane.
for practices, methods, and procedures A321–111, –112, –131, –211, –212, –213, (2) Within 900 flight cycles after the
the Administrator finds necessary for –231, and –232 airplanes, certificated in any effective date of this AD, without exceeding
safety in air commerce. This regulation category, manufacturer serial numbers 41,950 flight cycles since first installation of
is within the scope of that authority through 0758 inclusive. the door on an airplane.
(3) Within 50 flight cycles after the
because it addresses an unsafe condition (d) Subject effective date of this AD, for a door having
that is likely to exist or develop on Air Transport Association (ATA) of reached or exceeded 41,900 flight cycles
products identified in this rulemaking America Code 52, Doors. since first installation on an airplane.
action. (4) Within 3,000 flight cycles since the last
(e) Reason inspection of the door as specified in Airbus
Regulatory Findings This AD was prompted by a report of Service Bulletin A320–52–1032.
We determined that this proposed AD cracks on the frame forks and outer skin on
the forward and aft cargo compartment doors. (i) Corrective Actions
would not have federalism implications
We are issuing this AD to detect and correct If any crack is found during any inspection
under Executive Order 13132. This required by paragraph (h) of this AD, before
cracks on the frame forks and outer skin on
proposed AD would not have a the forward and aft cargo compartment doors, further flight, do all applicable corrective
substantial direct effect on the States, on which could lead to reduced structural actions in accordance with the
the relationship between the national integrity and failure of the cargo Accomplishment Instructions of SB A320–
Government and the States, or on the compartment door, possible decompression 52–1171 R01, except as specified in
distribution of power and of the airplane, and injury to occupants. paragraphs (k) and (l) of this AD.
responsibilities among the various Accomplishment of applicable corrective
(f) Compliance actions does not constitute terminating action
levels of government.
Comply with this AD within the for the repetitive inspections.
For the reasons discussed above, I compliance times specified, unless already
certify this proposed regulation: done. (j) Optional Terminating Action
1. Is not a ‘‘significant regulatory (1) Modification of all affected doors of an
action’’ under Executive Order 12866; (g) Definition of Affected Door airplane in accordance with the
2. Is not a ‘‘significant rule’’ under the For the purpose of this AD, an ‘‘affected Accomplishment Instructions of Airbus
DOT Regulatory Policies and Procedures door’’ is a forward or aft cargo compartment Service Bulletin A320–52–1042, Revision 2,
(44 FR 11034, February 26, 1979); door, having any part number listed in table dated January 14, 1997, constitutes
1 to paragraph (g) of this AD, except a cargo terminating action for the repetitive
3. Will not affect intrastate aviation in inspections specified in paragraph (h) of this
compartment door on which Airbus Service
Alaska; and Bulletin A320–52–1042 or Airbus Service AD for that airplane, provided that, after
4. Will not have a significant Bulletin A320–52–1170 is embodied. modification, no affected door is re-installed
economic impact, positive or negative, on that airplane.
on a substantial number of small entities TABLE 1 TO PARAGRAPH (g) OF THIS (2) Modification of all affected doors of an
under the criteria of the Regulatory airplane including accomplishment of all
AD—AFFECTED PART NUMBERS applicable related investigative and
Flexibility Act.
corrective actions in accordance with the
List of Subjects in 14 CFR Part 39 Aft cargo com- Accomplishment Instructions of Airbus
Forward cargo compart- partment door
ment door part Nos. Service Bulletin A320–52–1170, dated
Air transportation, Aircraft, Aviation part Nos.
September 5, 2016, except as specified in
safety, Incorporation by reference, paragraphs (k) and (l) of this AD, constitutes
Safety. D52371000000 D52371900000
D52371000002 D52371900002 terminating action for the repetitive
The Proposed Amendment D52371000004 D52371900004 inspections specified in paragraph (h) of this
D52371000006 D52371900008 AD for that airplane, provided that, after
Accordingly, under the authority D52371000008 D52371900010 modification, no affected door is re-installed
delegated to me by the Administrator, D52371000010 D52371900012 on that airplane.
the FAA proposes to amend 14 CFR part D52371000012 D52371900014 (3) Modification of all affected doors on an
39 as follows: D52371000014 D52371900016 airplane, in case of finding damaged frame
D52371000016 D52371900018 forks, as specified in an Airbus Repair Design
PART 39—AIRWORTHINESS D52371000018 D52371900022 Approval Sheet (RDAS), and done in
D52371000022 ............................ accordance with a method approved by the
DIRECTIVES Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
■ 1. The authority citation for part 39 (h) Repetitive Special Detailed Inspection of
European Aviation Safety Agency (EASA); or
continues to read as follows: Frame Forks
Airbus’s EASA Design Organization
Authority: 49 U.S.C. 106(g), 40113, 44701. At the latest of the compliance times listed Approval (DOA); constitutes terminating
in paragraphs (h)(1) through (h)(4) of this AD: action for the repetitive inspection specified
§ 39.13 [Amended] Do a special detailed inspection of all frame in paragraph (h) of this AD for that airplane,
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■ 2. The FAA amends § 39.13 by adding forks in the beam 4 area of any affected door provided that, after modification, no affected
as defined in paragraph (g) of this AD, in door is re-installed on that airplane.
the following new airworthiness accordance with the Accomplishment
directive (AD): Instructions of Airbus Service Bulletin A320– (k) Exception to Service Information
Airbus: Docket No. FAA–2017–0478; 52–1171, Revision 01, dated September 5, Where SB A320–52–1171 R01 specifies to
Directorate Identifier 2016–NM–174–AD. 2016 (‘‘SB A320–52–1171 R01’’), except as contact Airbus for appropriate action, and
specified in paragraphs (k) and (l) of this AD. specifies that action as ‘‘RC’’ (Required for
(a) Comments Due Date Repeat the inspection thereafter at intervals Compliance): Before further flight,
We must receive comments by July 6, 2017. not to exceed 3,000 flight cycles. A review of accomplish corrective actions in accordance
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![Federal Register / Vol. 82, No. 97 / Monday, May 22, 2017 / Proposed Rules 23163
with the procedures specified in paragraph airworthy condition. Any substitutions or proposing this AD to address the unsafe
(o)(2) of this AD. changes to procedures or tests identified as condition on these products.
RC require approval of an AMOC.
(l) No Reporting Requirement DATES: We must receive comments on
Although SB A320–52–1171 R01 specifies (p) Related Information this proposed AD by July 6, 2017.
to submit certain information to the (1) Refer to Mandatory Continuing ADDRESSES: You may send comments,
manufacturer, and specifies that action as Airworthiness Information (MCAI) EASA AD using the procedures found in 14 CFR
‘‘RC’’ (Required for Compliance), this AD 2016–0187, dated September 19, 2016, for 11.43 and 11.45, by any of the following
does not include that requirement. related information. This MCAI may be methods:
found in the AD docket on the Internet at
(m) Credit for Previous Actions • Federal eRulemaking Portal: Go to
http://www.regulations.gov by searching for
This paragraph provides credit for the and locating Docket No. FAA–2017–0478. http://www.regulations.gov. Follow the
actions required by paragraphs (h) and (i) of (2) For more information about this AD, instructions for submitting comments.
this AD, if those actions were performed contact Sanjay Ralhan, Aerospace Engineer, • Fax: 202–493–2251.
before the effective date of this AD using International Branch, ANM–116, Transport • Mail: U.S. Department of
Airbus Service Bulletin A320–52–1171, Airplane Directorate, FAA, 1601 Lind Transportation, Docket Operations, M–
dated October 29, 2015, provided that it can Avenue SW., Renton, WA 98057–3356; 30, West Building Ground Floor, Room
be conclusively determined that any part telephone: 425–227–1405; fax: 425–227– W12–140, 1200 New Jersey Avenue SE.,
number D52371000018 was also inspected as 1149.
specified in paragraph (h) of this AD.
Washington, DC 20590.
(3) For service information identified in • Hand Delivery: Deliver to Mail
(n) Parts Installation Limitation this AD, contact Airbus, Airworthiness— address above between 9 a.m. and 5
EIAS, 1 Rond Point Maurice Bellonte, 31707
As of the effective date of this AD, no Blagnac Cedex, France; telephone +33 5 61
p.m., Monday through Friday, except
person may install, on any airplane, an 93 36 96; fax +33 5 61 93 44 51; email Federal holidays.
affected door specified in paragraph (g) of account.airworth-eas@airbus.com; Internet For service information identified in
this AD, unless it has been inspected in this NPRM, contact Dassault Falcon Jet
http://www.airbus.com. You may view this
accordance with the requirements of Corporation, Teterboro Airport, P.O.
service information at the FAA, Transport
paragraph (h) of this AD and all applicable
corrective actions have been done in
Airplane Directorate, 1601 Lind Avenue SW., Box 2000, South Hackensack, NJ 07606;
Renton, WA. For information on the telephone 201–440–6700; Internet
accordance with paragraph (i) of this AD.
availability of this material at the FAA, call http://www.dassaultfalcon.com. You
(o) Other FAA AD Provisions 425–227–1221. may view this referenced service
The following provisions also apply to this Issued in Renton, Washington, on May 12, information at the FAA, Transport
AD: 2017. Airplane Directorate, 1601 Lind Avenue
(1) Alternative Methods of Compliance Michael Kaszycki, SW., Renton, WA. For information on
(AMOCs): The Manager, International
Branch, ANM–116, FAA, has the authority to Acting Manager, Transport Airplane the availability of this material at the
approve AMOCs for this AD, if requested Directorate, Aircraft Certification Service. FAA, call 425–227–1221.
using the procedures found in 14 CFR 39.19. [FR Doc. 2017–10138 Filed 5–19–17; 8:45 am]
Examining the AD Docket
In accordance with 14 CFR 39.19, send your BILLING CODE 4910–13–P
request to your principal inspector or local You may examine the AD docket on
Flight Standards District Office, as the Internet at http://
appropriate. If sending information directly DEPARTMENT OF TRANSPORTATION www.regulations.gov by searching for
to the manager of the International Branch, and locating Docket No. FAA–2017–
send it to the attention of the person Federal Aviation Administration 0475; or in person at the Docket
identified in paragraph (p)(2) of this AD.
Management Facility between 9 a.m.
Information may be emailed to: 9-ANM-116-
AMOC-REQUESTS@faa.gov. Before using
14 CFR Part 39 and 5 p.m., Monday through Friday,
any approved AMOC, notify your appropriate except Federal holidays. The AD docket
[Docket No. FAA–2017–0475; Directorate
principal inspector, or lacking a principal Identifier 2016–NM–142–AD] contains this proposed AD, the
inspector, the manager of the local flight regulatory evaluation, any comments
standards district office/certificate holding RIN 2120–AA64 received, and other information. The
district office. street address for the Docket Operations
(2) Contacting the Manufacturer: For any Airworthiness Directives; Dassault office (telephone 800–647–5527) is in
requirement in this AD to obtain corrective Aviation Airplanes the ADDRESSES section. Comments will
actions from a manufacturer, the action must
be accomplished using a method approved AGENCY: Federal Aviation be available in the AD docket shortly
by the Manager, International Branch, ANM– Administration (FAA), DOT. after receipt.
116, Transport Airplane Directorate, FAA; or ACTION: Notice of proposed rulemaking FOR FURTHER INFORMATION CONTACT: Tom
EASA; or Airbus’s EASA DOA. If approved Rodriguez, Aerospace Engineer,
by the DOA, the approval must include the
(NPRM).
International Branch, ANM–116,
DOA-authorized signature. SUMMARY: We propose to adopt a new Transport Airplane Directorate, FAA,
(3) Required for Compliance (RC): Except
as specified in paragraphs (k) and (l) of this airworthiness directive (AD) for all 1601 Lind Avenue SW., Renton, WA
AD: If any service information contains Dassault Aviation Model FALCON 2000 98057–3356; telephone 425–227–1137;
procedures or tests that are identified as RC, and FALCON 2000EX airplanes. This fax 425–227–1149.
those procedures and tests must be done to proposed AD was prompted by reports SUPPLEMENTARY INFORMATION:
comply with this AD; any procedures or tests of ice accretion on the airplane wing
Comments Invited
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that are not identified as RC are due to the failure of certain anti-ice
recommended. Those procedures and tests piccolo tubes in the wing outboard slats. We invite you to send any written
that are not identified as RC may be deviated This proposed AD would require relevant data, views, or arguments about
from using accepted methods in accordance
with the operator’s maintenance or repetitive inspections of each anti-ice this proposed AD. Send your comments
inspection program without obtaining piccolo tube and corrective action if to an address listed under the
approval of an AMOC, provided the necessary. This proposed AD also ADDRESSES section. Include ‘‘Docket No.
procedures and tests identified as RC can be provides an optional terminating action FAA–2017–0475; Directorate Identifier
done and the airplane can be put back in an for the repetitive inspections. We are 2016–NM–142–AD’’ at the beginning of
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Document Created: 2018-11-08 08:49:44
Document Modified: 2018-11-08 08:49:44
| 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 6, 2017. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1405; fax: 425-227-1149. | |
| FR Citation | 82 FR 23160 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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