80 FR 8513 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 32 (February 18, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 32 (February 18, 2015)
| Page Range | 8513-8516 | |
| FR Document | 2015-02697 |
[Federal Register Volume 80, Number 32 (Wednesday, February 18, 2015)] [Rules and Regulations] [Pages 8513-8516] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-02697] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2014-0484; Directorate Identifier 2013-NM-245-AD; Amendment 39-18101; AD 2015-03-05] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2012-09-07 for certain Airbus Model A319-111, -112, and -132 airplanes; Model A320- 111, -211, -212, -214, and -232 airplanes; and Model A321-111, -211, - 212, and -231 airplanes. AD 2012-09-07 required an electrical bonding test between the gravity fill re-fuel adaptor and the top skin panels on the wings; and, if necessary, an inspection for corrosion of the component interface and adjacent area; and repairing the gravity fuel adaptor if necessary. This new AD adds airplanes to the applicability and requires inspecting those airplanes to determine if a repair was done, and doing the electrical bonding test and corrective action if necessary. This AD was prompted by a determination that more airplanes are [[Page 8514]] subject to the identified unsafe condition. We are issuing this AD to detect and correct corrosion and improper bonding, which, in combination with a lightning strike in this area, could create a source of ignition in a fuel tank, resulting in a fire or explosion and consequent loss of the airplane. DATES: This AD becomes effective March 25, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 25, 2015. ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0484; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC. 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 referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014- 0484. 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: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2012-09-07, Amendment 39-17042 (77 FR 28238, May 14, 2012). AD 2012-09-07 applied to certain Airbus Model A319-111, -112, and -132 airplanes; Model A320-111, -211, -212, -214, and -232 airplanes; and Model A321-111, -211, -212, and -231 airplanes. The NPRM published in the Federal Register on July 30, 2014 (79 FR 44144). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2013-0277R1, dated December 4, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A318-111, -112, -121, and -122 airplanes; Model A319-111, -112, -113, - 114, -115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, - 211, -212, -213, -231, and -232 airplanes. The MCAI states: Cases of corrosion findings were reported on the overwing refueling aperture (used to fill the fuel tank by gravity) on the wing top skin. The reported corrosion was on the mating surface of the aperture flange, underneath the refuel adaptor. Corrosion findings have been repaired on a case by case basis in accordance with approved data. For certain aeroplanes, the repair provided by Airbus contained instructions to apply primer coating on the mating surface. Since doing those repairs, it has been found that this primer coating may prevent proper electrical bonding provision between the overwing refueling cap adaptor and the wing skin. This condition, if not detected and corrected, could, in combination with a lightning strike in this area, create a source of ignition in a fuel tank, possibly resulting in a fire or explosion and consequent loss of the aeroplane. To address this potential unsafe condition, EASA issued AD 2011- 0034 [http://ad.easa.europa.eu/blob/easa_ad_2011_0034.pdf/AD_2011-0034] to require a one-time electrical bonding check between the gravity fill re-fuel adaptor and the top skin panels on the affected aeroplanes (identified by MSN [manufacturer serial number] in the applicability section of that [EASA] AD) and, in case of findings, the accomplishment of applicable corrective actions. Since that [EASA] AD was issued, EASA has been made aware that some operators may inadvertently have applied an Airbus repair, approved for only one aeroplane MSN, to other aeroplanes, without requesting a revision of the repair to add aeroplanes, or to notify Airbus of such action(s). Consequently, the condition addressed by EASA AD 2011-0034 could affect more aeroplanes than initially determined. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2011-0034, which is superseded, and expands the Applicability to all A320 family aeroplane Models, all MSN. This [EASA] AD has been revised to amend and clarify paragraph (3), and to correct an error in the Type/Model designations on page 1, where the A318 was inadvertently omitted. For the newly added airplanes, required actions include inspecting for the presence of a corrosion repair on an overwing refueling aperture, and doing the electrical bonding test and applicable corrective actions if a repair has been installed. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0484-0002. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM (79 FR 44144, July 30, 2014) and the FAA's response to the comment. Request To Include Revised Service Information United Airlines (UAL) asked that we include a statement in the NPRM (79 FR 44144, July 30, 2014), which allows performing the required actions in accordance with the instructions of Airbus Service Bulletin A320-57-1152, Revision 01, dated December 19, 2013. UAL stated that the revised service information specifies the same method of inspection as specified in Airbus Service Bulletin A320-57-1152, dated June 14, 2010. UAL further stated that Revision 01 of this service bulletin also provides operators with updated repair instructions that were not available in the original issue of this service bulletin. We agree with the commenter's request. Since issuance of the NPRM (79 FR 44144, July 30, 2014), Airbus has issued Service Bulletin A320- 57-1152, Revision 01, dated December 19, 2013. This revision states that no additional work is necessary on airplanes changed in accordance with Airbus Service Bulletin A320-57-1152, dated June 14, 2010, which was specified as the appropriate source of service information in the NPRM (79 FR 44144, July 30, 2014). We have changed paragraph (g) of this AD to specify Airbus Service Bulletin A320-57-1152, Revision 01, dated December 19, 2013. We have also added a new paragraph (h) to this AD to give credit for actions done before the effective date of this AD using Airbus Service Bulletin A320-57-1152, dated June 14, 2010, and redesignated subsequent paragraphs accordingly. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM (79 FR 44144, July 30, 2014) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already [[Page 8515]] proposed in the NPRM (79 FR 44144, July 30, 2014). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320-57-1152, Revision 01, dated December 19, 2013. The service information describes procedures for inspecting certain airplanes to determine if a repair was done, and doing an electrical bonding test and corrective action if necessary. This service information is reasonably available; see ADDRESSES for ways to access this service information. Costs of Compliance We estimate that this AD affects 851 airplanes of U.S. registry. The actions required by AD 2012-09-07, Amendment 39-17042 (77 FR 28238, May 14, 2012), and retained in this AD take about 2 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that were required by AD 2012-09-07 is $170 per product. We also estimate that it takes about 2 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts cost about $0 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $144,670, or $170 per product. In addition, we estimate that any necessary follow-on actions will take about 11 work-hours, for a cost of $935 per product. We have no way of determining the number of aircraft that might need these actions. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0484; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647- 5527) is in the ADDRESSES section. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2012-09-07, Amendment 39-17042 (77 FR 28238, May 14, 2012), and adding the following new AD: 2015-03-05 Airbus: Amendment 39-18101. Docket No. FAA-2014-0484; Directorate Identifier 2013-NM-245-AD. (a) Effective Date This AD becomes effective March 25, 2015. (b) Affected ADs This AD replaces AD 2012-09-07, Amendment 39-17042 (77 FR 28238, May 14, 2012). (c) Applicability (1) This AD applies to Airbus Model A318-111, -112, -121, and - 122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-111, -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; all manufacturer serial numbers, except airplanes identified in paragraph (c)(2) of this AD. (2) Airplanes that have been delivered from production with Airbus Modification 38209 (Removal of the Outer Wing Refueling Aperture) incorporated, and without Airbus Modification 38206 (Re- introduction of the Outer Wing Refueling Aperture) incorporated, are not affected by the requirements of this AD. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a determination that more airplanes are subject to the identified unsafe condition. We are issuing this AD to detect and correct corrosion and improper bonding, which, in combination with a lightning strike in this area, could create a source of ignition in a fuel tank, resulting in a fire or explosion and consequent loss of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Electrical Bonding Test, and General Visual Inspection if Necessary, With Changes This paragraph restates the requirements of paragraph (g) of AD 2012-09-07, Amendment 39-17042 (77 FR 28238, May 14, 2012), with revised repair approval language and revised service information. For Model A319-111, -112, and -132 airplanes; Model A320-111, -211, -212, -214 and -232 airplanes; and Model A321-111, -211, -212, and - 231 airplanes; certificated in any category; having manufacturer serial numbers 0039, 0078, 0109, 0118, 0120, 0153, 0174, 0187, 0203, 0215, 0218, 0226, 0227, 0228, 0236, 0237, 0269, 0270, 0278, 0285, 0286, 0287, 0288, 0294, 0301, 0337, 0377, 0462, 0463, 0464, 0465, 0520, 0523, 0528, 0876, 0888, 0921, 0935, 0974, 1014, 1102, 1130, 1160, 1162, 1177, 1215, 1250, 1287, 1336, 1388, 1404, 1444, 1449, 1476, 1505, 1524, 1564, 1605, 1616, 1622, 1640, 1645, 1658, 1677, 1691, 1729, and 1905: Within 24 months after June 18, 2012 (the effective date of AD 2012-09-07), do an electrical bonding [[Page 8516]] test to check for bonding between the re-fuel adaptor of the gravity fill and the top skin panels on the left-hand and right-hand wings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1152, Revision 01, dated December 19, 2013. (1) If the resistance value is 10 milliohms or less at the left- hand and right-hand wing, no further action is required by this paragraph. (2) If the resistance value is greater than 10 milliohms at the left-hand or right-hand wing, before further flight, do a general visual inspection for corrosion of the component interface and adjacent area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1152, Revision 01, dated December 19, 2013. If any corrosion is found during the inspection, before further flight, repair the gravity fill fuel adaptor, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1152, Revision 01, dated December 19, 2013; except where Airbus Service Bulletin A320-57-1152, Revision 01, dated December 19, 2013, specifies to contact Airbus, before further flight, repair using a method approved by the Manager, International Branch, ANM- 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA- authorized signature. (h) Credit for Previous Actions This paragraph provides credit for the actions specified in paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-57- 1152, dated June 14, 2010, which was incorporated by reference in AD 2012-09-07, Amendment 39-17042 (77 FR 28238, May 14, 2012). (i) New Requirement of This AD: Maintenance Check/Electrical Bonding Test and Corrective Action if Necessary For airplanes other than those identified in paragraph (g) of this AD: Within 24 months after the effective date of this AD, determine whether a corrosion repair has been done on an overwing refueling aperture, whereby a primer coating has been applied on the mating surface of the aperture flange. A review of the airplane maintenance records is acceptable to make this determination, provided that whether a primer coat was applied can be conclusively determined from that review. (1) If it is determined that a primer coating was applied on the mating surface of the aperture flange; or if a determination cannot be made, or the outcome is inconclusive: Within 24 months after the effective date of this AD do the electrical bonding test specified in paragraph (g) of this AD, and before further flight, do all applicable actions specified in paragraph (g)(2) of this AD. (2) If it is determined that a corrosion repair has not been done, and a primer coating has not been applied on the mating surface of the aperture flange since first entry into service, no further action is required by this paragraph. (j) Corrosion Repair Provision As of the effective date of this AD, any corrosion repair done on an overwing refueling aperture on any airplane must comply with the repair requirements of paragraph (g)(2) of this AD. (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: 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]. (i) 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. (ii) AMOCs approved previously for AD 2012-09-07, Amendment 39- 17042 (77 FR 28238, May 14, 2012), are approved as AMOCs for the corresponding provisions of 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. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013-0277R1, dated December 4, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0484-0002. (2) Service information identified in this AD that is not incorporated by reference in this AD is available at the addresses specified in paragraphs (m)(4) and (m)(5) of this AD. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A320-57-1152, Revision 01, dated December 19, 2013. (ii) Reserved. (3) 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. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on February 4, 2015. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-02697 Filed 2-17-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations 8513
(7) For Model A340–541 and –642 incorporated by reference in AD 2007–22–10, (iii) Airbus Service Bulletin A340–57–
airplanes, repeat the inspections at intervals Amendment 39–15246 (72 FR 61796, 5009, Revision 03, dated October 17, 2013.
not to exceed 100 flight cycles or 500 flight November 1, 2007; corrected November 16, (3) For service information identified in
hours, whichever occurs first. 2007 (72 FR 64532)), on November 16, 2007. this AD, contact Airbus SAS, Airworthiness
(12) Airbus Service Bulletin A340–57– Office—EAL, 1 Rond Point Maurice Bellonte,
(h) Corrective Action 31707 Blagnac Cedex, France; telephone +33
5009, Revision 02, dated October 24, 2012,
If any cracking is found during any which is not incorporated by reference in this 5 61 93 36 96; fax +33 5 61 93 45 80; email
inspection required by paragraph (g) of this AD. airworthiness.A330-A340@airbus.com;
AD, before further flight, replace the cracked Internet http://www.airbus.com.
MLG support rib using a method approved by (j) Other FAA AD Provisions (4) You may view this service information
the Manager, International Branch, ANM– The following provisions also apply to this at the FAA, Transport Airplane Directorate,
116, Transport Airplane Directorate, FAA; or AD: 1601 Lind Avenue SW., Renton, WA. For
the European Aviation Safety Agency (1) Alternative Methods of Compliance information on the availability of this
(EASA); or Airbus’s EASA Design (AMOCs): The Manager, International material at the FAA, call 425–227–1221.
Organization Approval (DOA). If approved by Branch, ANM–116, Transport Airplane (5) You may view this service information
the DOA, the approval must include the Directorate, FAA, has the authority to that is incorporated by reference at the
DOA-authorized signature. Replacement of approve AMOCs for this AD, if requested National Archives and Records
an MLG support rib does not terminate the using the procedures found in 14 CFR 39.19. Administration (NARA). For information on
repetitive inspections required by paragraph In accordance with 14 CFR 39.19, send your the availability of this material at NARA, call
(g) of this AD. request to your principal inspector or local 202–741–6030, or go to: http://
Flight Standards District Office, as www.archives.gov/federal-register/cfr/ibr-
(i) Credit for Previous Actions
appropriate. If sending information directly locations.html.
This paragraph provides credit for the to the International Branch, send it to ATTN:
corresponding actions required by paragraph Issued in Renton, Washington, on February
Vladimir Ulyanov, Aerospace Engineer,
(g) of this AD, if those actions were 2, 2015.
International Branch, ANM–116, Transport
performed before the effective date of this AD Airplane Directorate, FAA, 1601 Lind Dionne Palermo,
using the applicable service bulletin Avenue SW., Renton, WA 98057–3356; Acting Manager, Transport Airplane
identified in paragraphs (i)(1) through (i)(12) telephone 425–227–1138; fax 425–227–1149. Directorate, Aircraft Certification Service.
of this AD. Information may be emailed to: 9-ANM-116- [FR Doc. 2015–02672 Filed 2–17–15; 8:45 am]
(1) Airbus Service Bulletin A330–57A3096, AMOC-REQUESTS@faa.gov. Before using BILLING CODE 4910–13–P
dated December 5, 2006, which was any approved AMOC, notify your appropriate
incorporated by reference in AD 2007–03–04, principal inspector, or lacking a principal
Amendment 39–14915 (72 FR 4416, January inspector, the manager of the local flight
31, 2007), on February 15, 2007. DEPARTMENT OF TRANSPORTATION
standards district office/certificate holding
(2) Airbus Service Bulletin A330–57A3096, district office. The AMOC approval letter
Revision 01, dated April 18, 2007, which is Federal Aviation Administration
must specifically reference this AD.
not incorporated by reference in this AD. (2) Contacting the Manufacturer: As of the
(3) Airbus Service Bulletin A330–57–3096, effective date of this AD, for any requirement 14 CFR Part 39
excluding appendix 01, Revision 02, dated in this AD to obtain corrective actions from
August 13, 2007, which was incorporated by [Docket No. FAA–2014–0484; Directorate
a manufacturer, the action must be
reference in AD 2007–22–10, Amendment Identifier 2013–NM–245–AD; Amendment
accomplished using a method approved by
39–15246 (72 FR 61796, November 1, 2007; 39–18101; AD 2015–03–05]
the Manager, International Branch, ANM–
corrected November 16, 2007 (72 FR 64532)), 116, Transport Airplane Directorate, FAA; or RIN 2120–AA64
on November 16, 2007. the European Aviation Safety Agency
(4) Airbus Service Bulletin A330–57–3096, (EASA); or Airbus’s EASA Design Airworthiness Directives; Airbus
Revision 03, dated October 24, 2012, which Organization Approval (DOA). If approved by
is not incorporated by reference in this AD.
Airplanes
the DOA, the approval must include the
(5) Airbus Service Bulletin A330–57–3096, DOA-authorized signature. AGENCY: Federal Aviation
Revision 04, dated February 6, 2013, which Administration (FAA), Department of
is not incorporated by reference in this AD. (k) Related Information
(6) Airbus Service Bulletin A340–57A4104,
Transportation (DOT).
(1) Refer to Mandatory Continuing
dated December 5, 2006, which was Airworthiness Information (MCAI) EASA ACTION: Final rule.
incorporated by reference in AD 2007–03–04, Airworthiness Directive 2013–0271, dated
Amendment 39–14915 (72 FR 4416, January November 14, 2013, for related information. SUMMARY: We are superseding
31, 2007), on February 15, 2007. You may examine the MCAI in the AD Airworthiness Directive (AD) 2012–09–
(7) Airbus Service Bulletin A340–57–4104, docket on the Internet at http:// 07 for certain Airbus Model A319–111,
Revision 01, dated August 13, 2007, which is www.regulations.gov/#!documentDetail;D= –112, and –132 airplanes; Model A320–
not incorporated by reference in this AD. FAA-2014-0620-0004. 111, –211, –212, –214, and –232
(8) Airbus Service Bulletin A340–57–4104, (2) Service information identified in this airplanes; and Model A321–111, –211,
excluding appendix 01, Revision 02, dated AD that is not incorporated by reference is –212, and –231 airplanes. AD 2012–09–
September 5, 2007, which was incorporated available at the addresses specified in
by reference in AD 2007–22–10, Amendment
07 required an electrical bonding test
paragraphs (l)(3) and (l)(4) of this AD.
39–15246 (72 FR 61796, November 1, 2007; between the gravity fill re-fuel adaptor
corrected November 16, 2007 (72 FR 64532)), (l) Material Incorporated by Reference and the top skin panels on the wings;
on November 16, 2007. (1) The Director of the Federal Register and, if necessary, an inspection for
(9) Airbus Service Bulletin A340–57–4104, approved the incorporation by reference corrosion of the component interface
Revision 03, dated October 24, 2012, which (IBR) of the service information listed in this and adjacent area; and repairing the
is not incorporated by reference in this AD. paragraph under 5 U.S.C. 552(a) and 1 CFR gravity fuel adaptor if necessary. This
mstockstill on DSK4VPTVN1PROD with RULES
(10) Airbus Service Bulletin A340– part 51. new AD adds airplanes to the
57A5009, dated December 5, 2006, which (2) You must use this service information
applicability and requires inspecting
was incorporated by reference in AD 2007– as applicable to do the actions required by
03–04, Amendment 39–14915 (72 FR 4416, this AD, unless this AD specifies otherwise. those airplanes to determine if a repair
January 31, 2007), on February 15, 2007. (i) Airbus Service Bulletin A330–57–3096, was done, and doing the electrical
(11) Airbus Service Bulletin A340–57– Revision 05, dated October 17, 2013. bonding test and corrective action if
5009, excluding appendix 01, Revision 01, (ii) Airbus Service Bulletin A340–57–4104, necessary. This AD was prompted by a
dated August 13, 2007, which was Revision 04, dated October 17, 2013. determination that more airplanes are
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subject to the identified unsafe Directive 2013–0277R1, dated December Internet at http://www.regulations.gov/#
condition. We are issuing this AD to 4, 2013 (referred to after this as the !documentDetail;D=FAA-2014-0484-
detect and correct corrosion and Mandatory Continuing Airworthiness 0002.
improper bonding, which, in Information, or ‘‘the MCAI’’), to correct
Comments
combination with a lightning strike in an unsafe condition for all Airbus
this area, could create a source of Model A318–111, –112, –121, and –122 We gave the public the opportunity to
ignition in a fuel tank, resulting in a fire airplanes; Model A319–111, –112, –113, participate in developing this AD. The
or explosion and consequent loss of the –114, –115, –131, –132, and –133 following presents the comment
airplane. airplanes; Model A320–111, –211, –212, received on the NPRM (79 FR 44144,
DATES: This AD becomes effective –214, –231, –232, and –233 airplanes; July 30, 2014) and the FAA’s response
March 25, 2015. and Model A321–111, –112, –131, –211, to the comment.
The Director of the Federal Register –212, –213, –231, and –232 airplanes.
Request To Include Revised Service
approved the incorporation by reference The MCAI states:
Information
of a certain publication listed in this AD Cases of corrosion findings were reported
as of March 25, 2015. on the overwing refueling aperture (used to United Airlines (UAL) asked that we
ADDRESSES: You may examine the AD fill the fuel tank by gravity) on the wing top include a statement in the NPRM (79 FR
docket on the Internet at http:// skin. The reported corrosion was on the 44144, July 30, 2014), which allows
www.regulations.gov/#!docketDetail;D= mating surface of the aperture flange, performing the required actions in
underneath the refuel adaptor. Corrosion accordance with the instructions of
FAA-2014-0484; or in person at the findings have been repaired on a case by case
Docket Management Facility, U.S. Airbus Service Bulletin A320–57–1152,
basis in accordance with approved data.
Department of Transportation, Docket Revision 01, dated December 19, 2013.
For certain aeroplanes, the repair provided
Operations, M–30, West Building by Airbus contained instructions to apply UAL stated that the revised service
Ground Floor, Room W12–140, 1200 primer coating on the mating surface. Since information specifies the same method
New Jersey Avenue SE., Washington, doing those repairs, it has been found that of inspection as specified in Airbus
DC. this primer coating may prevent proper Service Bulletin A320–57–1152, dated
For service information identified in electrical bonding provision between the June 14, 2010. UAL further stated that
this AD, contact Airbus, Airworthiness overwing refueling cap adaptor and the wing Revision 01 of this service bulletin also
skin. provides operators with updated repair
Office—EIAS, 1 Rond Point Maurice This condition, if not detected and
Bellonte, 31707 Blagnac Cedex, France; instructions that were not available in
corrected, could, in combination with a
telephone +33 5 61 93 36 96; fax +33 5 lightning strike in this area, create a source the original issue of this service
61 93 44 51; email account.airworth- of ignition in a fuel tank, possibly resulting bulletin.
eas@airbus.com; Internet http:// in a fire or explosion and consequent loss of We agree with the commenter’s
www.airbus.com. You may view this the aeroplane. request. Since issuance of the NPRM (79
referenced service information at the To address this potential unsafe condition, FR 44144, July 30, 2014), Airbus has
FAA, Transport Airplane Directorate, EASA issued AD 2011–0034 [http:// issued Service Bulletin A320–57–1152,
ad.easa.europa.eu/blob/easa_ad_2011_ Revision 01, dated December 19, 2013.
1601 Lind Avenue SW., Renton, WA. 0034.pdf/AD_2011-0034] to require a one-
For information on the availability of time electrical bonding check between the
This revision states that no additional
this material at the FAA, call 425–227– gravity fill re-fuel adaptor and the top skin work is necessary on airplanes changed
1221. It is also available on the Internet panels on the affected aeroplanes (identified in accordance with Airbus Service
at http://www.regulations.gov by by MSN [manufacturer serial number] in the Bulletin A320–57–1152, dated June 14,
searching for and locating Docket No. applicability section of that [EASA] AD) and, 2010, which was specified as the
FAA–2014–0484. in case of findings, the accomplishment of appropriate source of service
applicable corrective actions. information in the NPRM (79 FR 44144,
FOR FURTHER INFORMATION CONTACT:
Since that [EASA] AD was issued, EASA July 30, 2014).
Sanjay Ralhan, Aerospace Engineer, has been made aware that some operators
International Branch, ANM–116, may inadvertently have applied an Airbus We have changed paragraph (g) of this
Transport Airplane Directorate, FAA, repair, approved for only one aeroplane AD to specify Airbus Service Bulletin
1601 Lind Avenue SW., Renton, WA MSN, to other aeroplanes, without requesting A320–57–1152, Revision 01, dated
98057–3356; telephone 425–227–1405; a revision of the repair to add aeroplanes, or December 19, 2013. We have also added
fax 425–227–1149. to notify Airbus of such action(s). a new paragraph (h) to this AD to give
Consequently, the condition addressed by credit for actions done before the
SUPPLEMENTARY INFORMATION:
EASA AD 2011–0034 could affect more effective date of this AD using Airbus
Discussion aeroplanes than initially determined. Service Bulletin A320–57–1152, dated
For the reasons described above, this
We issued a notice of proposed June 14, 2010, and redesignated
[EASA] AD retains the requirements of EASA
rulemaking (NPRM) to amend 14 CFR AD 2011–0034, which is superseded, and subsequent paragraphs accordingly.
part 39 to supersede AD 2012–09–07, expands the Applicability to all A320 family Conclusion
Amendment 39–17042 (77 FR 28238, aeroplane Models, all MSN.
May 14, 2012). AD 2012–09–07 applied This [EASA] AD has been revised to amend We reviewed the relevant data and
to certain Airbus Model A319–111, and clarify paragraph (3), and to correct an determined that air safety and the
–112, and –132 airplanes; Model A320– error in the Type/Model designations on page public interest require adopting this AD
111, –211, –212, –214, and –232 1, where the A318 was inadvertently omitted. with the changes described previously
airplanes; and Model A321–111, –211, For the newly added airplanes, required and minor editorial changes. We have
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–212, and –231 airplanes. The NPRM actions include inspecting for the determined that these minor changes:
published in the Federal Register on presence of a corrosion repair on an • Are consistent with the intent that
July 30, 2014 (79 FR 44144). overwing refueling aperture, and doing was proposed in the NPRM (79 FR
The European Aviation Safety Agency the electrical bonding test and 44144, July 30, 2014) for correcting the
(EASA), which is the Technical Agent applicable corrective actions if a repair unsafe condition; and
for the Member States of the European has been installed. You may examine • Do not add any additional burden
Union, has issued EASA Airworthiness the MCAI in the AD docket on the upon the public than was already
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![Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations 8515
proposed in the NPRM (79 FR 44144, because it addresses an unsafe condition 2015–03–05 Airbus: Amendment 39–18101.
July 30, 2014). that is likely to exist or develop on Docket No. FAA–2014–0484; Directorate
We also determined that these products identified in this rulemaking Identifier 2013–NM–245–AD.
changes will not increase the economic action. (a) Effective Date
burden on any operator or increase the This AD becomes effective March 25, 2015.
scope of this AD. Regulatory Findings
We determined that this AD will not (b) Affected ADs
Related Service Information Under 1 have federalism implications under This AD replaces AD 2012–09–07,
CFR Part 51 Executive Order 13132. This AD will Amendment 39–17042 (77 FR 28238, May 14,
Airbus has issued Service Bulletin not have a substantial direct effect on 2012).
A320–57–1152, Revision 01, dated the States, on the relationship between (c) Applicability
December 19, 2013. The service the national government and the States, (1) This AD applies to Airbus Model A318–
information describes procedures for or on the distribution of power and 111, –112, –121, and –122 airplanes; Model
inspecting certain airplanes to responsibilities among the various A319–111, –112, –113, –114, –115, –131,
determine if a repair was done, and levels of government. –132, and –133 airplanes; Model A320–111,
doing an electrical bonding test and For the reasons discussed above, I –211, –212, –214, –231, –232, and –233
corrective action if necessary. This certify that this AD: airplanes; and Model A321–111, –112, –131,
service information is reasonably 1. Is not a ‘‘significant regulatory –211, –212, –213, –231, and –232 airplanes;
available; see ADDRESSES for ways to action’’ under Executive Order 12866; certificated in any category; all manufacturer
serial numbers, except airplanes identified in
access this service information. 2. Is not a ‘‘significant rule’’ under the paragraph (c)(2) of this AD.
DOT Regulatory Policies and Procedures (2) Airplanes that have been delivered from
Costs of Compliance
(44 FR 11034, February 26, 1979); production with Airbus Modification 38209
We estimate that this AD affects 851 3. Will not affect intrastate aviation in (Removal of the Outer Wing Refueling
airplanes of U.S. registry. Alaska; and Aperture) incorporated, and without Airbus
The actions required by AD 2012–09– 4. Will not have a significant Modification 38206 (Re-introduction of the
07, Amendment 39–17042 (77 FR economic impact, positive or negative, Outer Wing Refueling Aperture)
28238, May 14, 2012), and retained in on a substantial number of small entities incorporated, are not affected by the
this AD take about 2 work-hours per under the criteria of the Regulatory requirements of this AD.
product, at an average labor rate of $85 Flexibility Act. (d) Subject
per work-hour. Based on these figures, Air Transport Association (ATA) of
the estimated cost of the actions that Examining the AD Docket
America Code 57, Wings.
were required by AD 2012–09–07 is You may examine the AD docket on
$170 per product. (e) Reason
the Internet at http://
We also estimate that it takes about 2 www.regulations.gov/#!docketDetail;D= This AD was prompted by a determination
work-hours per product to comply with FAA-2014-0484; or in person at the that more airplanes are subject to the
the basic requirements of this AD. The identified unsafe condition. We are issuing
Docket Management Facility between 9
this AD to detect and correct corrosion and
average labor rate is $85 per work-hour. a.m. and 5 p.m., Monday through improper bonding, which, in combination
Required parts cost about $0 per Friday, except Federal holidays. The AD with a lightning strike in this area, could
product. Based on these figures, we docket contains this AD, the regulatory create a source of ignition in a fuel tank,
estimate the cost of this AD on U.S. evaluation, any comments received, and resulting in a fire or explosion and
operators to be $144,670, or $170 per other information. The street address for consequent loss of the airplane.
product. the Docket Operations office (telephone (f) Compliance
In addition, we estimate that any 800–647–5527) is in the ADDRESSES
necessary follow-on actions will take Comply with this AD within the
section. compliance times specified, unless already
about 11 work-hours, for a cost of $935
List of Subjects in 14 CFR Part 39 done.
per product. We have no way of
determining the number of aircraft that Air transportation, Aircraft, Aviation (g) Retained Electrical Bonding Test, and
might need these actions. safety, Incorporation by reference, General Visual Inspection if Necessary, With
Safety. Changes
Authority for This Rulemaking This paragraph restates the requirements of
Title 49 of the United States Code Adoption of the Amendment paragraph (g) of AD 2012–09–07,
specifies the FAA’s authority to issue Accordingly, under the authority Amendment 39–17042 (77 FR 28238, May 14,
rules on aviation safety. Subtitle I, delegated to me by the Administrator, 2012), with revised repair approval language
section 106, describes the authority of and revised service information. For Model
the FAA amends 14 CFR part 39 as A319–111, –112, and –132 airplanes; Model
the FAA Administrator. ‘‘Subtitle VII: follows: A320–111, –211, –212, –214 and –232
Aviation Programs,’’ describes in more airplanes; and Model A321–111, –211, –212,
detail the scope of the Agency’s PART 39—AIRWORTHINESS and –231 airplanes; certificated in any
authority. DIRECTIVES category; having manufacturer serial numbers
We are issuing this rulemaking under 0039, 0078, 0109, 0118, 0120, 0153, 0174,
the authority described in ‘‘Subtitle VII, ■ 1. The authority citation for part 39 0187, 0203, 0215, 0218, 0226, 0227, 0228,
Part A, Subpart III, Section 44701: continues to read as follows: 0236, 0237, 0269, 0270, 0278, 0285, 0286,
General requirements.’’ Under that Authority: 49 U.S.C. 106(g), 40113, 44701. 0287, 0288, 0294, 0301, 0337, 0377, 0462,
mstockstill on DSK4VPTVN1PROD with RULES
section, Congress charges the FAA with 0463, 0464, 0465, 0520, 0523, 0528, 0876,
§ 39.13 [Amended] 0888, 0921, 0935, 0974, 1014, 1102, 1130,
promoting safe flight of civil aircraft in
1160, 1162, 1177, 1215, 1250, 1287, 1336,
air commerce by prescribing regulations ■ 2. The FAA amends § 39.13 by 1388, 1404, 1444, 1449, 1476, 1505, 1524,
for practices, methods, and procedures removing Airworthiness Directive (AD) 1564, 1605, 1616, 1622, 1640, 1645, 1658,
the Administrator finds necessary for 2012–09–07, Amendment 39–17042 (77 1677, 1691, 1729, and 1905: Within 24
safety in air commerce. This regulation FR 28238, May 14, 2012), and adding months after June 18, 2012 (the effective date
is within the scope of that authority the following new AD: of AD 2012–09–07), do an electrical bonding
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![8516 Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations
test to check for bonding between the re-fuel (j) Corrosion Repair Provision (ii) Reserved.
adaptor of the gravity fill and the top skin As of the effective date of this AD, any (3) For service information identified in
panels on the left-hand and right-hand wings, corrosion repair done on an overwing this AD, contact Airbus, Airworthiness
in accordance with the Accomplishment refueling aperture on any airplane must Office—EIAS, 1 Rond Point Maurice
Instructions of Airbus Service Bulletin A320– comply with the repair requirements of Bellonte, 31707 Blagnac Cedex, France;
57–1152, Revision 01, dated December 19, paragraph (g)(2) of this AD. telephone +33 5 61 93 36 96; fax +33 5 61
2013. 93 44 51; email account.airworth-eas@
(1) If the resistance value is 10 milliohms (k) Other FAA AD Provisions airbus.com; Internet http://www.airbus.com.
or less at the left-hand and right-hand wing, The following provisions also apply to this (4) You may view this service information
no further action is required by this AD: at the FAA, Transport Airplane Directorate,
paragraph. (1) Alternative Methods of Compliance 1601 Lind Avenue SW., Renton, WA. For
(2) If the resistance value is greater than 10 (AMOCs): The Manager, International information on the availability of this
milliohms at the left-hand or right-hand Branch, ANM–116, Transport Airplane material at the FAA, call 425–227–1221.
wing, before further flight, do a general visual Directorate, FAA, has the authority to (5) You may view this service information
inspection for corrosion of the component approve AMOCs for this AD, if requested that is incorporated by reference at the
interface and adjacent area, in accordance using the procedures found in 14 CFR 39.19. National Archives and Records
with the Accomplishment Instructions of In accordance with 14 CFR 39.19, send your Administration (NARA). For information on
Airbus Service Bulletin A320–57–1152, request to your principal inspector or local the availability of this material at NARA, call
Revision 01, dated December 19, 2013. If any Flight Standards District Office, as 202–741–6030, or go to: http://
corrosion is found during the inspection, www.archives.gov/federal-register/cfr/ibr-
appropriate. If sending information directly
before further flight, repair the gravity fill locations.html.
to the International Branch, send it to ATTN:
fuel adaptor, in accordance with the Sanjay Ralhan, Aerospace Engineer, Issued in Renton, Washington, on February
Accomplishment Instructions of Airbus International Branch, ANM–116, Transport 4, 2015.
Service Bulletin A320–57–1152, Revision 01, Airplane Directorate, FAA, 1601 Lind
dated December 19, 2013; except where Dionne Palermo,
Avenue SW., Renton, WA 98057–3356; Acting Manager, Transport Airplane
Airbus Service Bulletin A320–57–1152,
telephone 425–227–1405; fax 425–227–1149. Directorate, Aircraft Certification Service.
Revision 01, dated December 19, 2013,
Information may be emailed to: 9-ANM-116-
specifies to contact Airbus, before further [FR Doc. 2015–02697 Filed 2–17–15; 8:45 am]
AMOC-REQUESTS@faa.gov.
flight, repair using a method approved by the BILLING CODE 4910–13–P
(i) Before using any approved AMOC,
Manager, International Branch, ANM–116,
notify your appropriate principal inspector,
Transport Airplane Directorate, FAA; or the
or lacking a principal inspector, the manager
European Aviation Safety Agency (EASA); or DEPARTMENT OF TRANSPORTATION
of the local flight standards district office/
Airbus’s EASA Design Organization
certificate holding district office. The AMOC
Approval (DOA). If approved by the DOA, Federal Aviation Administration
approval letter must specifically reference
the approval must include the DOA-
authorized signature. this AD.
(ii) AMOCs approved previously for AD 14 CFR Part 39
(h) Credit for Previous Actions 2012–09–07, Amendment 39–17042 (77 FR
28238, May 14, 2012), are approved as [Docket No. FAA–2014–0522; Directorate
This paragraph provides credit for the Identifier 2014–NM–087–AD; Amendment
actions specified in paragraph (g) of this AD, AMOCs for the corresponding provisions of
this AD. 39–18100; AD 2015–03–04]
if those actions were performed before the
effective date of this AD using Airbus Service (2) Contacting the Manufacturer: As of the RIN 2120–AA64
Bulletin A320–57–1152, dated June 14, 2010, effective date of this AD, for any requirement
which was incorporated by reference in AD in this AD to obtain corrective actions from Airworthiness Directives; The Boeing
2012–09–07, Amendment 39–17042 (77 FR a manufacturer, the action must be Company Airplanes
28238, May 14, 2012). accomplished using a method approved by
the Manager, International Branch, ANM– AGENCY: Federal Aviation
(i) New Requirement of This AD: 116, Transport Airplane Directorate, FAA; or Administration (FAA), DOT.
Maintenance Check/Electrical Bonding Test EASA; or Airbus’s EASA DOA. If approved
and Corrective Action if Necessary ACTION: Final rule.
by the DOA, the approval must include the
For airplanes other than those identified in DOA-authorized signature. SUMMARY: We are adopting a new
paragraph (g) of this AD: Within 24 months airworthiness directive (AD) for certain
(l) Related Information
after the effective date of this AD, determine The Boeing Company Model 747–100,
whether a corrosion repair has been done on (1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA 747–100B, 747–100B SUD, 747–200B,
an overwing refueling aperture, whereby a
primer coating has been applied on the Airworthiness Directive 2013–0277R1, dated 747–200C, 747–200F, 747–300, 747–
mating surface of the aperture flange. A December 4, 2013, for related information. 400, 747–400D, 747–400F, 747SR, and
review of the airplane maintenance records is This MCAI may be found in the AD docket 747SP series airplanes. This AD was
acceptable to make this determination, on the Internet at prompted by reports of fuselage skin
provided that whether a primer coat was http://www.regulations.gov/#!document cracks at the lower forward corner of the
applied can be conclusively determined from Detail;D=FAA-2014-0484-0002. main entry door (MED) 1 cutout. This
that review. (2) Service information identified in this AD requires repetitive inspections of the
(1) If it is determined that a primer coating AD that is not incorporated by reference in
fuselage skin of the MED 1 cutout for
was applied on the mating surface of the this AD is available at the addresses specified
aperture flange; or if a determination cannot in paragraphs (m)(4) and (m)(5) of this AD. cracking, and repair if necessary; and
be made, or the outcome is inconclusive: also provides an optional terminating
(m) Material Incorporated by Reference modification, including post-repair or
Within 24 months after the effective date of
this AD do the electrical bonding test (1) The Director of the Federal Register post-modification fuselage skin
specified in paragraph (g) of this AD, and approved the incorporation by reference inspections for cracking, and corrective
mstockstill on DSK4VPTVN1PROD with RULES
before further flight, do all applicable actions (IBR) of the service information listed in this actions if necessary. We are issuing this
specified in paragraph (g)(2) of this AD. paragraph under 5 U.S.C. 552(a) and 1 CFR AD to detect and correct skin cracking,
(2) If it is determined that a corrosion part 51.
which can become large and could
repair has not been done, and a primer (2) You must use this service information
coating has not been applied on the mating as applicable to do the actions required by adversely affect the structural integrity
surface of the aperture flange since first entry this AD, unless this AD specifies otherwise. of the airplane.
into service, no further action is required by (i) Airbus Service Bulletin A320–57–1152, DATES: This AD is effective March 25,
this paragraph. Revision 01, dated December 19, 2013. 2015.
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Document Created: 2018-02-16 11:10:45
Document Modified: 2018-02-16 11:10:45
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD becomes effective March 25, 2015. | |
| 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 | 80 FR 8513 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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