81 FR 51813 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 151 (August 5, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 151 (August 5, 2016)
| Page Range | 51813-51815 | |
| FR Document | 2016-18492 |
[Federal Register Volume 81, Number 151 (Friday, August 5, 2016)] [Proposed Rules] [Pages 51813-51815] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-18492] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-8185; Directorate Identifier 2016-NM-050-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2003-18- 06, for certain Airbus Model A319-131 and -132 airplanes; Model A320- 231, -232, and -233 airplanes; and Model A321-131 and -231 airplanes. AD 2003-18-06 currently requires installing new anti-swivel plates and weights on the engine fan cowl door (FCD) latches and a new cowl door hold-open device. Since we issued AD 2003-18-06, we have received reports of additional engine FCD in-flight losses, and a new FCD front latch and keeper assembly has been developed to address this unsafe condition. This proposed AD would retain the current actions and require modifying the engine FCDs, installing placards, and re- identifying the FCDs with the new part numbers. This proposed AD would also revise the applicability to include all Model A319-131 and -132 airplanes; Model A320-231, -232, and -233 airplanes; and Model A321-131 and -231 airplanes. We are proposing this AD to prevent in-flight loss of an engine FCD and possible consequent damage to the airplane and hazards to persons or property on the ground. DATES: We must receive comments on this proposed AD by September 19, 2016. ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC, 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-2016- 8185; 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-2016-8185; Directorate Identifier 2016-NM-050-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 On August 29, 2003, we issued AD 2003-18-06, Amendment 39-13297 (68 FR 53501, September 11, 2003) (``AD 2003-18-06''). AD 2003-18-06 requires actions intended to address an unsafe condition on certain Airbus Model A319-131 and -132 airplanes; Model A320-231, -232, and - 233 airplanes; and Model A321-131 and -231 airplanes. Since we issued AD 2003-18-06, we have received reports of additional engine FCD in-flight losses, and a new FCD front latch and keeper assembly has been developed to address this unsafe condition. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2016-0053, dated March 14, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A319-131 and -132; A320-231, -232, and -233; and A321-131 and -231 airplanes. The MCAI states: Fan Cowl Door (FCD) losses during take-off were reported on aeroplanes equipped with IAE V2500 engines. Prompted by these occurences, [Direction G[eacute]n[eacute]rale de l'Aviation Civile] DGAC France issued AD 2000-444-156(B), mandating FCD latch improvements. This [DGAC] AD was later superseded by AD 2001-381(B) [which corresponds to FAA AD 2003-18-06], requiring installation of additional fan cowl latch improvement by installing a hold open device. Since that [DGAC] AD was issued, further FCD in flight losses were experienced in service. Investigations confirmed that in all [[Page 51814]] cases, the fan cowls were opened prior to the flight and were not correctly re-secured. During the pre-flight inspection, it was then not detected that the FCD were not properly latched. This condition, if not corrected, could lead to in-flight loss of a FCD, possibly resulting in damage to the aeroplane and/or injury to persons on the ground. Prompted by these recent events, new FCD front latch and keeper assembly were developed, having a specific key necessary to un-latch the FCD. This key cannot be removed unless the FCD front latch is safely closed. The key, after removal, must be stowed in the flight deck at a specific location, as instructed in the applicable Aircraft Maintenance Manual. Applicable Flight Crew Operating Manual has been amended accordingly. After modification, the FCD is identified with a different Part Number (P/N). For the reasons described above, this [EASA] AD retains the requirements of DGAC AD 2001-381(B), which is superseded, and requires modification and re-identification of FCD. 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- 8185. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320-71-1069, dated December 18, 2015. The service information describes procedures for modifying the engine FCDs, installing placards, and re-identifying the FCDs with the new part numbers. 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 558 airplanes of U.S. registry. The actions required by AD 2003-18-06, and retained in this proposed AD, take about 8 work-hours per product, at an average labor rate of $85 per work-hour. Required parts cost about $1,500 per product. Based on these figures, the estimated cost of the actions that are required by AD 2003-18-06 is $2,180 per product. We also estimate that it would take about 6 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $4,813 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $2,970,234, or $5,323 per product. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this 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 removing Airworthiness Directive (AD) 2003-18-06, Amendment 39-13297 (68 FR 53501, September 11, 2003), and adding the following new AD: Airbus: Docket No. FAA-2016-8185; Directorate Identifier 2016-NM- 050-AD. (a) Comments Due Date We must receive comments by September 19, 2016. (b) Affected ADs This AD replaces AD 2003-18-06, Amendment 39-13297 (68 FR 53501, September 11, 2003) (``AD 2003-18-06''). (c) Applicability This AD applies to Airbus Model A319-131 and -132 airplanes; Model A320-231, -232, and -233 airplanes; and Model A321-131 and - 231 airplanes; certificated in any category; all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) Reason This AD was prompted by reports of engine fan cowl door (FCD) in-flight losses. We are issuing this AD to prevent in-flight loss of an engine FCD and possible consequent damage to the airplane and hazards to persons or property on the ground. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Modification and/or Installation, With No Changes This paragraph restates the requirements of paragraph (a) of AD 2003-18-06, with no changes. Within 18 months after October 16, 2003 (the effective date of AD 2003-18-06), do the action(s) specified in paragraph (g)(1) or (g)(2) of this AD, as applicable. (1) For Configuration 01 airplanes identified in Airbus Service Bulletin A320-71-1028, dated March 23, 2001: Modify the door latches of the fan cowl of both engines (i.e., installation of new anti- swivel plates and weights), and install a new hold-open [[Page 51815]] device, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-71-1028, dated March 23, 2001. (2) For Configuration 02 airplanes identified in Airbus Service Bulletin A320-71-1028, dated March 23, 2001: Install a new hold-open device, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-71-1028, dated March 23, 2001. (h) New Modifications Within 36 months after the effective date of this AD, do the actions required by paragraphs (h)(1), (h)(2), and (h)(3) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-71-1069, dated December 18, 2015. (1) Modify the left-hand and right-hand FCDs on engines 1 and 2. (2) Install a placard on the box located at the bottom of the 120 VU panel or at the bottom of the coat stowage, as applicable. (3) Re-identify both engine FCDs with the new part numbers (P/ Ns), as specified in table 1 to paragraph (h) of this AD and table 2 to paragraph (h) of this AD, as applicable. Table 1 to Paragraph (h) of This AD--Left-Side Door ------------------------------------------------------------------------ Old part No. New part No. ------------------------------------------------------------------------ 740-4000-501......................................... 740-4000-9501 740-4000-503......................................... 740-4000-9503 745-4000-501......................................... 745-4000-513 745-4000-503......................................... 745-4000-515 745-4000-505......................................... 745-4000-517 ------------------------------------------------------------------------ Table 2 to Paragraph (h) of This AD--Right-Side Door ------------------------------------------------------------------------ Old part No. New part No. ------------------------------------------------------------------------ 740-4000-502......................................... 740-4000-9502 740-4000-504......................................... 740-4000-9504 740-4000-506......................................... 740-4000-9506 740-4000-508......................................... 740-4000-9508 745-4000-502......................................... 745-4000-9502 745-4000-504......................................... 745-4000-9504 745-4000-506......................................... 745-4000-9506 745-4000-508......................................... 745-4000-514 745-4000-510......................................... 745-4000-516 745-4000-512......................................... 745-4000-518 ------------------------------------------------------------------------ (i) New Alternative Compliance (1) Replacing an engine FCD having a part number listed as ``Old Part Number'' in table 1 to paragraph (h) of this AD or table 2 to paragraph (h) of this AD, as applicable, with a FCD having the corresponding part number listed as ``New Part Number'' in table 1 to paragraph (h) of this AD or table 2 to paragraph (h) of this AD, as applicable, is an acceptable method of compliance with the requirements of paragraphs (h)(1) and (h)(3) of this AD for that engine FCD only. (2) An airplane on which Airbus Modification 157516 has been embodied in production is compliant with the requirements of paragraph (h)(1) and (h)(3) of this AD, provided no engine FCD, having a part number identified as ``Old Part Number'' in table 1 to paragraph (h) of this AD or table 2 to paragraph (h) of this AD, as applicable, is installed on that airplane. (3) An airplane on which Airbus Modification 157718 has been embodied in production is compliant with the requirements of paragraph (h)(2) of this AD. (j) New Parts Installation Limitations (1) For an airplane with an engine FCD installed having a part number identified as ``Old Part Number'' in table 1 to paragraph (h) of this AD or table 2 to paragraph (h) of this AD, as applicable: After modification of that airplane as required by paragraph (h) of this AD, do not install an engine FCD, having a part number identified as ``Old Part Number'' in table 1 to paragraph (h) of this AD or table 2 to paragraph (h) of this AD, as applicable. (2) For an airplane that does not have an engine FCD installed having a part number identified as ``Old Part Number'' in table 1 to paragraph (h) of this AD or table 2 to paragraph (h) of this AD, as applicable: On or after the effective date of this AD, do not install an engine FCD, having a part number identified as ``Old Part Number'' in table 1 to paragraph (h) of this AD or table 2 to paragraph (h) of this AD, as applicable. (k) New Method of Compliance Installation on an engine of a right-hand and left-hand engine FCD having a part number approved after the effective date of this AD is a method of compliance with the requirements of paragraphs (g), (h)(1), and (h)(3) of this AD for that engine only, provided the part number is approved, and the installation is accomplished, 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). (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, 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: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by 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 (k) 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 2016-0053, dated March 14, 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-2016-8185. (2) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. 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 26, 2016. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-18492 Filed 8-4-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 151 / Friday, August 5, 2016 / Proposed Rules 51813
0026. After carefully considering the applicability to include all Model 98057–3356; telephone: 425–227–1405;
requests for additional time, DOE has A319–131 and –132 airplanes; Model fax: 425–227–1149.
determined that a reopening of the A320–231, –232, and –233 airplanes; SUPPLEMENTARY INFORMATION:
public comment period is appropriate, and Model A321–131 and –231
based upon the foregoing reasons. DOE airplanes. We are proposing this AD to Comments Invited
believes that reopening the comment prevent in-flight loss of an engine FCD We invite you to send any written
period until August 30, 2016 will and possible consequent damage to the relevant data, views, or arguments about
provide the public with sufficient time airplane and hazards to persons or this proposed AD. Send your comments
to submit comments responding to property on the ground. to an address listed under the
DOE’s proposed energy conservation DATES: We must receive comments on ADDRESSES section. Include ‘‘Docket No.
standards. Accordingly, DOE is this proposed AD by September 19, FAA–2016–8185; Directorate Identifier
reopening the comment period to 2016. 2016–NM–050–AD’’ at the beginning of
midnight of August 30, 2016 and will your comments. We specifically invite
deem any comments received by that ADDRESSES: You may send comments by comments on the overall regulatory,
date to be timely submitted. DOE further any of the following methods: economic, environmental, and energy
notes that any submissions of comments • Federal eRulemaking Portal: Go to aspects of this proposed AD. We will
or other information submitted between http://www.regulations.gov. Follow the consider all comments received by the
the original comment end date and the instructions for submitting comments. closing date and may amend this
reopening of the comment period will • Fax: 202–493–2251. proposed AD based on those comments.
be deemed timely filed. • Mail: U.S. Department of We will post all comments we
Transportation, Docket Operations, receive, without change, to http://
Issued in Washington, DC, on July 28,
2016. M–30, West Building Ground Floor, www.regulations.gov, including any
Room W12–140, 1200 New Jersey personal information you provide. We
Kathleen B. Hogan,
Avenue SE., Washington, DC 20590. will also post a report summarizing each
Deputy Assistant Secretary for Energy
Efficiency, Energy Efficiency and Renewable • Hand Delivery: U.S. Department of substantive verbal contact we receive
Energy. Transportation, Docket Operations, about this proposed AD.
[FR Doc. 2016–18674 Filed 8–4–16; 8:45 am] M–30, West Building Ground Floor, Discussion
Room W12–140, 1200 New Jersey
BILLING CODE 6450–01–P
Avenue SE., Washington, DC, between 9 On August 29, 2003, we issued AD
a.m. and 5 p.m., Monday through 2003–18–06, Amendment 39–13297 (68
Friday, except Federal holidays. FR 53501, September 11, 2003) (‘‘AD
DEPARTMENT OF TRANSPORTATION 2003–18–06’’). AD 2003–18–06 requires
For service information identified in
this NPRM, contact Airbus, actions intended to address an unsafe
Federal Aviation Administration condition on certain Airbus Model
Airworthiness Office—EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac A319–131 and –132 airplanes; Model
14 CFR Part 39 A320–231, –232, and –233 airplanes;
Cedex, France; telephone +33 5 61 93 36
[Docket No. FAA–2016–8185; Directorate 96; fax +33 5 61 93 44 51; email and Model A321–131 and –231
Identifier 2016–NM–050–AD] account.airworth-eas@airbus.com; airplanes.
Internet http://www.airbus.com. You Since we issued AD 2003–18–06, we
RIN 2120–AA64
may view this referenced service have received reports of additional
Airworthiness Directives; Airbus information at the FAA, Transport engine FCD in-flight losses, and a new
Airplanes Airplane Directorate, 1601 Lind Avenue FCD front latch and keeper assembly
SW., Renton, WA. For information on has been developed to address this
AGENCY: Federal Aviation unsafe condition.
Administration (FAA), DOT. the availability of this material at the
The European Aviation Safety Agency
FAA, call 425–227–1221.
ACTION: Notice of proposed rulemaking (EASA), which is the Technical Agent
(NPRM). Examining the AD Docket for the Member States of the European
Union, has issued EASA Airworthiness
SUMMARY: We propose to supersede You may examine the AD docket on
Directive 2016–0053, dated March 14,
Airworthiness Directive (AD) 2003–18– the Internet at http://
2016 (referred to after this as the
06, for certain Airbus Model A319–131 www.regulations.gov by searching for
Mandatory Continuing Airworthiness
and –132 airplanes; Model A320–231, and locating Docket No. FAA–2016–
Information, or ‘‘the MCAI’’), to correct
–232, and –233 airplanes; and Model 8185; or in person at the Docket
an unsafe condition for all Airbus
A321–131 and –231 airplanes. AD Management Facility between 9 a.m.
Model A319–131 and –132; A320–231,
2003–18–06 currently requires installing and 5 p.m., Monday through Friday,
–232, and –233; and A321–131 and
new anti-swivel plates and weights on except Federal holidays. The AD docket
–231 airplanes. The MCAI states:
the engine fan cowl door (FCD) latches contains this proposed AD, the
regulatory evaluation, any comments Fan Cowl Door (FCD) losses during take-off
and a new cowl door hold-open device. were reported on aeroplanes equipped with
Since we issued AD 2003–18–06, we received, and other information. The
IAE V2500 engines. Prompted by these
have received reports of additional street address for the Docket Operations
occurences, [Direction Générale de l’Aviation
engine FCD in-flight losses, and a new office (telephone 800–647–5527) is in Civile] DGAC France issued AD 2000–444–
mstockstill on DSK3G9T082PROD with PROPOSALS
FCD front latch and keeper assembly the ADDRESSES section. Comments will 156(B), mandating FCD latch improvements.
has been developed to address this be available in the AD docket shortly This [DGAC] AD was later superseded by AD
unsafe condition. This proposed AD after receipt. 2001–381(B) [which corresponds to FAA AD
would retain the current actions and FOR FURTHER INFORMATION CONTACT:
2003–18–06], requiring installation of
additional fan cowl latch improvement by
require modifying the engine FCDs, Sanjay Ralhan, Aerospace Engineer, installing a hold open device.
installing placards, and re-identifying International Branch, ANM–116, Since that [DGAC] AD was issued, further
the FCDs with the new part numbers. Transport Airplane Directorate, FAA, FCD in flight losses were experienced in
This proposed AD would also revise the 1601 Lind Avenue SW., Renton, WA service. Investigations confirmed that in all
VerDate Sep<11>2014 16:15 Aug 04, 2016 Jkt 238001 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 E:\FR\FM\05AUP1.SGM 05AUP1](https://thefederalregister.org/doc/81_FR_51964/page/1.svg)
![51814 Federal Register / Vol. 81, No. 151 / Friday, August 5, 2016 / Proposed Rules
cases, the fan cowls were opened prior to the an average labor rate of $85 per work- List of Subjects in 14 CFR Part 39
flight and were not correctly re-secured. hour. Required parts cost about $1,500
During the pre-flight inspection, it was then Air transportation, Aircraft, Aviation
per product. Based on these figures, the safety, Incorporation by reference,
not detected that the FCD were not properly estimated cost of the actions that are
latched. Safety.
This condition, if not corrected, could lead
required by AD 2003–18–06 is $2,180
per product. The Proposed Amendment
to in-flight loss of a FCD, possibly resulting
in damage to the aeroplane and/or injury to We also estimate that it would take Accordingly, under the authority
persons on the ground. about 6 work-hours per product to delegated to me by the Administrator,
Prompted by these recent events, new FCD comply with the basic requirements of the FAA proposes to amend 14 CFR part
front latch and keeper assembly were this proposed AD. The average labor 39 as follows:
developed, having a specific key necessary to rate is $85 per work-hour. Required
un-latch the FCD. This key cannot be PART 39—AIRWORTHINESS
removed unless the FCD front latch is safely
parts would cost about $4,813 per
product. Based on these figures, we DIRECTIVES
closed. The key, after removal, must be
stowed in the flight deck at a specific estimate the cost of this proposed AD on
■ 1. The authority citation for part 39
location, as instructed in the applicable U.S. operators to be $2,970,234, or
continues to read as follows:
Aircraft Maintenance Manual. Applicable $5,323 per product.
Flight Crew Operating Manual has been Authority: 49 U.S.C. 106(g), 40113, 44701.
amended accordingly. After modification, the Authority for This Rulemaking
FCD is identified with a different Part § 39.13 [Amended]
Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by
Number (P/N).
specifies the FAA’s authority to issue removing Airworthiness Directive (AD)
For the reasons described above, this
[EASA] AD retains the requirements of DGAC rules on aviation safety. Subtitle I, 2003–18–06, Amendment 39–13297 (68
AD 2001–381(B), which is superseded, and section 106, describes the authority of FR 53501, September 11, 2003), and
requires modification and re-identification of the FAA Administrator. ‘‘Subtitle VII: adding the following new AD:
FCD. Aviation Programs,’’ describes in more
detail the scope of the Agency’s Airbus: Docket No. FAA–2016–8185;
You may examine the MCAI in the AD Directorate Identifier 2016–NM–050–AD.
docket on the Internet at http:// authority.
We are issuing this rulemaking under (a) Comments Due Date
www.regulations.gov by searching for
and locating Docket No. FAA–2016– the authority described in ‘‘Subtitle VII, We must receive comments by September
8185. Part A, Subpart III, Section 44701: 19, 2016.
General requirements.’’ Under that (b) Affected ADs
Related Service Information Under 1 section, Congress charges the FAA with
CFR Part 51 This AD replaces AD 2003–18–06,
promoting safe flight of civil aircraft in Amendment 39–13297 (68 FR 53501,
Airbus has issued Service Bulletin air commerce by prescribing regulations September 11, 2003) (‘‘AD 2003–18–06’’).
A320–71–1069, dated December 18, for practices, methods, and procedures
the Administrator finds necessary for (c) Applicability
2015. The service information describes
procedures for modifying the engine safety in air commerce. This regulation This AD applies to Airbus Model A319–
is within the scope of that authority 131 and –132 airplanes; Model A320–231,
FCDs, installing placards, and re-
because it addresses an unsafe condition –232, and –233 airplanes; and Model A321–
identifying the FCDs with the new part 131 and –231 airplanes; certificated in any
numbers. This service information is that is likely to exist or develop on category; all manufacturer serial numbers.
reasonably available because the products identified in this rulemaking
interested parties have access to it action. (d) Subject
through their normal course of business Air Transport Association (ATA) of
Regulatory Findings America Code 71, Powerplant.
or by the means identified in the
ADDRESSES section. We determined that this proposed AD (e) Reason
would not have federalism implications
FAA’s Determination and Requirements This AD was prompted by reports of
under Executive Order 13132. This engine fan cowl door (FCD) in-flight losses.
of This Proposed AD proposed AD would not have a We are issuing this AD to prevent in-flight
This product has been approved by substantial direct effect on the States, on loss of an engine FCD and possible
the aviation authority of another the relationship between the national consequent damage to the airplane and
country, and is approved for operation Government and the States, or on the hazards to persons or property on the ground.
in the United States. Pursuant to our distribution of power and (f) Compliance
bilateral agreement with the State of responsibilities among the various
Design Authority, we have been notified Comply with this AD within the
levels of government.
compliance times specified, unless already
of the unsafe condition described in the For the reasons discussed above, I done.
MCAI and service information certify this proposed regulation:
referenced above. We are proposing this (g) Retained Modification and/or
1. Is not a ‘‘significant regulatory Installation, With No Changes
AD because we evaluated all pertinent action’’ under Executive Order 12866;
information and determined an unsafe This paragraph restates the requirements of
2. Is not a ‘‘significant rule’’ under the paragraph (a) of AD 2003–18–06, with no
condition exists and is likely to exist or
DOT Regulatory Policies and Procedures changes. Within 18 months after October 16,
develop on other products of these same
mstockstill on DSK3G9T082PROD with PROPOSALS
(44 FR 11034, February 26, 1979); 2003 (the effective date of AD 2003–18–06),
type designs.
3. Will not affect intrastate aviation in do the action(s) specified in paragraph (g)(1)
Costs of Compliance Alaska; and or (g)(2) of this AD, as applicable.
(1) For Configuration 01 airplanes
We estimate that this proposed AD 4. Will not have a significant identified in Airbus Service Bulletin A320–
affects 558 airplanes of U.S. registry. economic impact, positive or negative, 71–1028, dated March 23, 2001: Modify the
The actions required by AD 2003–18– on a substantial number of small entities door latches of the fan cowl of both engines
06, and retained in this proposed AD, under the criteria of the Regulatory (i.e., installation of new anti-swivel plates
take about 8 work-hours per product, at Flexibility Act. and weights), and install a new hold-open
VerDate Sep<11>2014 16:15 Aug 04, 2016 Jkt 238001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 E:\FR\FM\05AUP1.SGM 05AUP1](https://thefederalregister.org/doc/81_FR_51964/page/2.svg)
![Federal Register / Vol. 81, No. 151 / Friday, August 5, 2016 / Proposed Rules 51815
device, in accordance with the in table 1 to paragraph (h) of this AD or table a manufacturer, the action must be
Accomplishment Instructions of Airbus 2 to paragraph (h) of this AD, as applicable, accomplished using a method approved by
Service Bulletin A320–71–1028, dated March is installed on that airplane. the Manager, International Branch, ANM–
23, 2001. (3) An airplane on which Airbus 116, Transport Airplane Directorate, FAA; or
(2) For Configuration 02 airplanes Modification 157718 has been embodied in EASA; or Airbus’s EASA DOA. If approved
identified in Airbus Service Bulletin A320– production is compliant with the by the DOA, the approval must include the
71–1028, dated March 23, 2001: Install a new requirements of paragraph (h)(2) of this AD. DOA-authorized signature.
hold-open device, in accordance with the (3) Required for Compliance (RC): Except
(j) New Parts Installation Limitations as required by paragraph (k) of this AD, if any
Accomplishment Instructions of Airbus
Service Bulletin A320–71–1028, dated March (1) For an airplane with an engine FCD service information contains procedures or
23, 2001. installed having a part number identified as tests that are identified as RC, those
‘‘Old Part Number’’ in table 1 to paragraph procedures and tests must be done to comply
(h) New Modifications (h) of this AD or table 2 to paragraph (h) of with this AD; any procedures or tests that are
Within 36 months after the effective date this AD, as applicable: After modification of not identified as RC are recommended. Those
of this AD, do the actions required by that airplane as required by paragraph (h) of procedures and tests that are not identified
paragraphs (h)(1), (h)(2), and (h)(3) of this this AD, do not install an engine FCD, having as RC may be deviated from using accepted
AD, in accordance with the Accomplishment a part number identified as ‘‘Old Part methods in accordance with the operator’s
Instructions of Airbus Service Bulletin A320– Number’’ in table 1 to paragraph (h) of this maintenance or inspection program without
71–1069, dated December 18, 2015. AD or table 2 to paragraph (h) of this AD, as obtaining approval of an AMOC, provided
(1) Modify the left-hand and right-hand applicable. the procedures and tests identified as RC can
FCDs on engines 1 and 2. (2) For an airplane that does not have an be done and the airplane can be put back in
(2) Install a placard on the box located at engine FCD installed having a part number an airworthy condition. Any substitutions or
the bottom of the 120 VU panel or at the identified as ‘‘Old Part Number’’ in table 1 changes to procedures or tests identified as
bottom of the coat stowage, as applicable. to paragraph (h) of this AD or table 2 to RC require approval of an AMOC.
(3) Re-identify both engine FCDs with the paragraph (h) of this AD, as applicable: On
(m) Related Information
new part numbers (P/Ns), as specified in or after the effective date of this AD, do not
table 1 to paragraph (h) of this AD and table install an engine FCD, having a part number (1) Refer to Mandatory Continuing
2 to paragraph (h) of this AD, as applicable. identified as ‘‘Old Part Number’’ in table 1 Airworthiness Information (MCAI) EASA
to paragraph (h) of this AD or table 2 to Airworthiness Directive 2016–0053, dated
paragraph (h) of this AD, as applicable. March 14, 2016, for related information. This
TABLE 1 TO PARAGRAPH (h) OF THIS MCAI may be found in the AD docket on the
AD—LEFT-SIDE DOOR (k) New Method of Compliance Internet at http://www.regulations.gov by
Installation on an engine of a right-hand searching for and locating Docket No. FAA–
Old part No. New part No. and left-hand engine FCD having a part 2016–8185.
number approved after the effective date of (2) For service information identified in
740–4000–501 ................ 740–4000–9501 this AD is a method of compliance with the this AD, contact Airbus, Airworthiness
740–4000–503 ................ 740–4000–9503 requirements of paragraphs (g), (h)(1), and Office—EIAS, 1 Rond Point Maurice
745–4000–501 ................ 745–4000–513 (h)(3) of this AD for that engine only, Bellonte, 31707 Blagnac Cedex, France;
745–4000–503 ................ 745–4000–515 provided the part number is approved, and telephone +33 5 61 93 36 96; fax +33 5 61
745–4000–505 ................ 745–4000–517 the installation is accomplished, in 93 44 51; email account.airworth-eas@
accordance with a method approved by the airbus.com; Internet http://www.airbus.com.
Manager, International Branch, ANM–116, You may view this service information at the
TABLE 2 TO PARAGRAPH (h) OF THIS Transport Airplane Directorate, FAA; or the FAA, Transport Airplane Directorate, 1601
AD—RIGHT-SIDE DOOR European Aviation Safety Agency (EASA); or Lind Avenue SW., Renton, WA. For
Airbus’s EASA Design Organization information on the availability of this
Old part No. New part No. Approval (DOA). material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on July 26,
740–4000–502 ................ 740–4000–9502 (l) Other FAA AD Provisions 2016.
740–4000–504 ................ 740–4000–9504 The following provisions also apply to this Victor Wicklund,
740–4000–506 ................ 740–4000–9506 AD:
Acting Manager, Transport Airplane
740–4000–508 ................ 740–4000–9508 (1) Alternative Methods of Compliance
Directorate, Aircraft Certification Service.
745–4000–502 ................ 745–4000–9502 (AMOCs): The Manager, International
745–4000–504 ................ 745–4000–9504 Branch, ANM–116, FAA, has the authority to [FR Doc. 2016–18492 Filed 8–4–16; 8:45 am]
745–4000–506 ................ 745–4000–9506 approve AMOCs for this AD, if requested BILLING CODE 4910–13–P
745–4000–508 ................ 745–4000–514 using the procedures found in 14 CFR 39.19.
745–4000–510 ................ 745–4000–516 In accordance with 14 CFR 39.19, send your
745–4000–512 ................ 745–4000–518 request to your principal inspector or local DEPARTMENT OF TRANSPORTATION
Flight Standards District Office, as
(i) New Alternative Compliance appropriate. If sending information directly Federal Aviation Administration
to the International Branch, send it to ATTN:
(1) Replacing an engine FCD having a part Sanjay Ralhan, Aerospace Engineer,
number listed as ‘‘Old Part Number’’ in table International Branch, ANM–116, Transport 14 CFR Part 39
1 to paragraph (h) of this AD or table 2 to Airplane Directorate, FAA, 1601 Lind [Docket No. FAA–2015–3143; Directorate
paragraph (h) of this AD, as applicable, with Avenue SW., Renton, WA 98057–3356; Identifier 2015–NM–047–AD]
a FCD having the corresponding part number telephone: 425–227–1405; fax: 425–227–
listed as ‘‘New Part Number’’ in table 1 to 1149. Information may be emailed to: 9- RIN 2120–AA64
paragraph (h) of this AD or table 2 to ANM-116-AMOC-REQUESTS@faa.gov.
paragraph (h) of this AD, as applicable, is an Before using any approved AMOC, notify Airworthiness Directives; Empresa
mstockstill on DSK3G9T082PROD with PROPOSALS
acceptable method of compliance with the your appropriate principal inspector, or Brasileira de Aeronautica S.A.
requirements of paragraphs (h)(1) and (h)(3) lacking a principal inspector, the manager of (Embraer) Airplanes
of this AD for that engine FCD only. the local flight standards district office/
(2) An airplane on which Airbus certificate holding district office. The AMOC AGENCY: Federal Aviation
Modification 157516 has been embodied in approval letter must specifically reference Administration (FAA), DOT.
production is compliant with the this AD. ACTION: Supplemental notice of
requirements of paragraph (h)(1) and (h)(3) of (2) Contacting the Manufacturer: As of the proposed rulemaking (NPRM);
this AD, provided no engine FCD, having a effective date of this AD, for any requirement
part number identified as ‘‘Old Part Number’’
reopening of comment period.
in this AD to obtain corrective actions from
VerDate Sep<11>2014 16:15 Aug 04, 2016 Jkt 238001 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 E:\FR\FM\05AUP1.SGM 05AUP1](https://thefederalregister.org/doc/81_FR_51964/page/3.svg)
Document Created: 2016-08-05 06:43:57
Document Modified: 2016-08-05 06:43:57
| 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 September 19, 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 51813 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR