81 FR 63370 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 179 (September 15, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 179 (September 15, 2016)
| Page Range | 63370-63374 | |
| FR Document | 2016-21146 |
[Federal Register Volume 81, Number 179 (Thursday, September 15, 2016)] [Rules and Regulations] [Pages 63370-63374] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-21146] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-6550; Directorate Identifier 2013-NM-162-AD; Amendment 39-18638; AD 2016-18-08] 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) 90-11-05 for certain Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4- 203 airplanes and Model A300 B4-600 series airplanes. AD 90-11-05 required repetitive detailed inspections for cracking in the aft hinge brackets of the outer shroud box that is located in the outer wing box, and related investigative and corrective actions if necessary. This new AD changes certain compliance times and adds airplanes to the applicability. This AD was prompted by reports of cracks in the aft hinge brackets of the outer shroud box that is located in the outer wing box, which were found during routine maintenance checks, and our subsequent determination that a change in inspection compliance times is needed. We are issuing this AD to detect and correct cracking of the aft hinge brackets of the outer shroud box; such cracking could affect the structural integrity of the airplane. DATES: This AD becomes effective October 20, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 20, 2016. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office--EAW, 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-2015- 6550. 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-2015- 6550; 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 address for the Docket Office (telephone 800- 647-5527) is 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 20590. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA [[Page 63371]] 98057-3356; telephone 425-227-2125; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 90-11-05, Amendment 39-6603 (89-NM-223-AD) (55 FR 20129, May 15, 1990) (``AD 90-11-05''). AD 90-11-05 applied to certain Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4 203 airplanes and Model A300 B4-600 series airplanes. The NPRM published in the Federal Register on December 14, 2015 (80 FR 77279) (``the NPRM''). The NPRM was prompted by a determination that a change to certain compliance times is needed. The NPRM proposed to continue to require doing repetitive detailed inspections for cracking in the hinge brackets of the forward and aft outer shroud boxes that are located in the outer wing box, and related investigative and corrective actions if necessary. The NPRM also proposed to change certain compliance times and add airplanes to the applicability. We are issuing this AD to detect and correct cracking of the aft hinge brackets of the outer shroud box; such cracking could affect the structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2013-0181R1, dated August 20, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Model A300 series airplanes and Model A300 B4-600 series airplanes. The MCAI states: In the past, aft hinge brackets of the outer wing box were found cracked. Fracture of a bracket would allow vertical movement of the inner shroud box structure, which could result in damage to the top skin of the inboard flap. In addition, the loads carried by the brackets will be transferred to the remaining supports, which may also crack and cause extensive structural damage. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. To address this potential unsafe condition, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France issued * * * [an airworthiness directive] (later revised) to require repetitive inspections of the hinge bracket of the outer box and, depending on findings, corrective action(s). Since that [DGAC] AD was issued, a fleet survey and updated Fatigue and Damage Tolerance analysis were performed in order to substantiate the A300 Extended Service Goal (ESG) and A300-600 Extended Service Goal (ESG2) exercise. The results of these analyses led to a change in the inspection thresholds and intervals in Flight Cycles (FC) and the introduction of Flight Hours (FH) limits. For the reasons described above, this [EASA] AD retains the requirements of DGAC France * * * [an airworthiness directive], which is superseded, but requires those actions within the new thresholds and intervals given by Airbus Service Bulletin (SB) A300- 57-0142 Revision 04 or A300-57-6010 Revision 05, as applicable to aeroplane model. Revision 1 of this [EASA] AD is issued to add model A300 B4-203 aeroplanes to the applicability and compliance time tables. This model is covered by Airbus SB A300-57-0142, but was mistakenly omitted from the original [EASA] AD issue. The corrective action for a hinge bracket that is cracked or fractured is replacing the damaged hinge bracket with a new bracket. For airplanes on which a crack is found in one half bracket or both half brackets, related investigative actions include a general visual inspection for secondary damage (e.g., cracks, wear damage, pitting, and gouging) in the following areas:The inner shroud-box forward attachments and the attachment brackets at the inboard end. The inner and outer shroud-box structure, adjacent to the fractured bracket. The top skin of the inboard flap. The corrective action for damage findings during the related investigative action is repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA Design Organization Approval (DOA). The compliance time for related investigative actions and corrective actions is before further flight. 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-2015- 6550. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM and the FAA's response to the comment. Request To Exclude Certain Airplanes From the Applicability FedEx requested that we exclude from the proposed applicability airplanes on which the actions specified in Airbus Service Bulletin A300-57-6011, Revision 2, dated July 10, 1989, have been accomplished. FedEx stated that it has accomplished the optional terminating actions provided in paragraph (j)(1) of the proposed AD, and specified in Airbus Service Bulletin A300-57-6011, Revision 2, dated July 10, 1989, on several of its airplanes. We disagree with FedEx's request. As of the effective date of this AD, additional actions are required for airplanes on which the optional modification has been accomplished. These airplanes will need to have a one-time detailed visual inspection of the forward and aft outer shroud box with no cracking found, as required by paragraph (j)(2) of this AD. We have not changed this AD in this regard. Changes Made to This AD In paragraph (j)(2) of the proposed AD, we proposed to provide an optional method of compliance (i.e., a replacement and a one-time inspection) for actions specified in paragraph (g) of the proposed AD. We also proposed to give credit in paragraph (k)(2) of the proposed AD for replacements accomplished before the effective date of this AD using the same service information identified in paragraph (j)(2) of the AD: Airbus Service Bulletin A300-57-143, dated December 17, 1986. Airbus Service Bulletin A300-57-143, Revision 1, dated March 19, 1987. Airbus Service Bulletin A300-57-6011, dated December 17, 1986. Airbus Service Bulletin A300-57-6011, Revision 1, dated March 19, 1987. Since we cannot make this service information reasonably available, we have revised paragraph (j)(2) of the proposed AD, removed redundant paragraph (k)(2) of the proposed AD from this AD, and redesignated paragraph (k)(1) and subsequent subparagraphs accordingly. We revised paragraph (j)(2) of this AD by removing the references to the service information and instead specified that operators must do the replacement using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA Design Organization Approval (DOA). Conclusion We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes: Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and [[Page 63372]] Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. Airbus Service Bulletin A300-57-0142, Revision 04, dated March 30, 2011, which describes procedures for doing an inspection of the forward and aft hinge brackets on the outer shroud box. Airbus Service Bulletin A300-57-143, Revision 2, dated July 10, 1989, which describes procedures for replacing the aft aluminum alloy brackets on the outer shroud box with new steel brackets. Airbus Service Bulletin A300-57-6010, Revision 05, dated February 21, 2011, which describes procedures for doing an inspection of the forward and aft hinge brackets on the outer shroud box. Airbus Service Bulletin A300-57-6011, Revision 2, dated July 10, 1989, which describes procedures for replacing the aft aluminum alloy brackets on the outer shroud box with new steel brackets. 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. Costs of Compliance We estimate that this AD affects 3 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspection..................... 8 work-hours x $85 per $0 $680 per $2,040 per hour = $680 per inspection cycle. inspection cycle. inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary replacements that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these replacements: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Replacement................................ 27 work-hours x $85 per hour = $25,650 $27,945 $2,295. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition related investigative and corrective actions specified in this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this 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. 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) 90-11-05, Amendment 39-6603 (89-NM-223-AD) (55 FR 20129, May 15, 1990), and adding the following new AD: 2016-18-08 Airbus: Amendment 39-18638. Docket No. FAA-2015-6550; Directorate Identifier 2013-NM-162-AD. (a) Effective Date This AD becomes effective October 20, 2016. (b) Affected ADs This AD replaces AD 90-11-05, Amendment 39-6603 (89-NM-223-AD) (55 FR 20129, May 15, 1990). (c) Applicability This AD applies to Airbus Model A300 B2-1C, B2K-3C, B2-203, B4- 2C, B4-103, and B4-203 airplanes; Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; and Model A300 B4-605R airplanes; certificated in any category; except airplanes on which Airbus Modification 6661 has been embodied during production. [[Page 63373]] (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by reports of cracks in the aft hinge brackets of the outer shroud box that is located in the outer wing box, which were found during routine maintenance checks, and our subsequent determination that a change in inspection compliance times is needed. We are issuing this AD to detect and correct cracking of the aft hinge brackets of the outer shroud box; such cracking could affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections At the applicable compliance time specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD: Do a detailed inspection for cracks and fractures of the hinge brackets of the forward and aft outer shroud boxes, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0142, Revision 04, dated March 30, 2011; or Airbus Service Bulletin A300-57-6010, Revision 05, dated February 21, 2011; as applicable. Repeat the inspection thereafter at the applicable interval specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0142, Revision 04, dated March 30, 2011; or Airbus Service Bulletin A300-57-6010, Revision 05, dated February 21, 2011; as applicable. Doing the replacement specified in paragraph (j) of this AD terminates the repetitive inspections required by this paragraph. (1) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, B4- 2C, and B4-203 airplanes: Do the inspection at the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. Repeat the inspection thereafter at intervals not to exceed 1,000 flight cycles or 2,000 flight hours, whichever occurs first. (i) Before the accumulation of 5,000 flight cycles or 10,400 flight hours since first flight, whichever occurs first. (ii) Within 100 flight cycles after the effective date of this AD. (2) For Model A300 B2-1C, B2-203, and B2K-3C airplanes: Do the inspection at the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. Repeat the inspection thereafter at intervals not to exceed 1,000 flight cycles or 1,000 flight hours, whichever occurs first. (i) Before the accumulation of 5,000 flight cycles or 5,400 flight hours since first flight, whichever occurs first. (ii) Within 100 flight cycles after the effective date of this AD. (3) For Model A300 B4-103 airplanes: Do the inspection at the later of the times specified in paragraphs (g)(3)(i) and (g)(3)(ii) of this AD. Repeat the inspection thereafter at intervals not to exceed 1,000 flight cycles or 1,300 flight hours, whichever occurs first. (i) Before the accumulation of 5,000 flight cycles or 6,600 flight hours since first flight, whichever occurs first. (ii) Within 100 flight cycles after the effective date of this AD. (h) Corrective Action If any crack or fracture is found during any inspection required by paragraph (g) of this AD: Before further flight, replace the damaged hinge bracket with a new bracket, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-143, Revision 2, dated July 10, 1989; or Airbus A300-57-6011, Revision 2, dated July 10, 1989; as applicable. (i) Related Investigative and Corrective Actions If any crack or fracture is found during any inspection required by paragraph (g) of this AD: Before further flight, do a general visual inspection for secondary damage (e.g., cracks, wear damage, pitting, and gouging) in the areas specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0142, Revision 04, dated March 30, 2011; or Airbus Service Bulletin A300-57-6010, Revision 05, dated February 21, 2011; as applicable. If any damage is found, 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). (1) The inner shroud-box forward attachments and the attachment brackets at the inboard end. (2) The inner and outer shroud-box structure, adjacent to the fractured bracket. (3) The top skin of the inboard flap. (j) Optional Terminating Action for Inspection Requirements of Paragraph (g) of This AD (1) Replacement of the hinge bracket, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-143, Revision 2, dated July 10, 1989 (for Model A300 series airplanes); or Airbus Service Bulletin A300-57-6011, Revision 2, dated July 10, 1989; as applicable; terminates the inspection requirements of paragraph (g) of this AD (for Model A300 B4-600 series airplanes). (2) Replacement of a hinge bracket before the effective date of this AD terminates the repetitive inspections required by paragraph (g) of this AD, provided that after the hinge bracket replacement, but before further flight after the effective date of this AD, a one-time detailed inspection of the forward and aft outer shroud box has been done with no cracking found, in accordance with paragraph (g) of this AD. The replacement must be done in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (k) Credit for Previous Actions This paragraph provides credit for inspections required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using any of the applicable service information listed in paragraphs (k)(1) through (k)(8) of this AD. (1) Airbus Service Bulletin A300-57-142, dated December 17, 1986. (2) Airbus Service Bulletin A300-57-142, Revision 1, dated April 9, 1990. (3) Airbus Service Bulletin A300-57-142, Revision 2, dated January 16, 1991. (4) Airbus Service Bulletin A300-57-0142, Revision 03, dated February 22, 1999. (5) Airbus Service Bulletin A300-57-6010, Revision 1, dated December 14, 1990. (6) Airbus Service Bulletin A300-57-6010, Revision 02, dated March 30, 1998. (7) Airbus Service Bulletin A300-57-6010, Revision 03, dated September 16, 1998. (8) Airbus Service Bulletin A300-57-6010, Revision 04, dated February 22, 1999. (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-2125; 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. (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; EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013-0181R1, dated August 20, 2013, 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-2015-6550. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (n)(3) and (n)(4) of this AD. (n) 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. [[Page 63374]] (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 A300-57-0142, Revision 04, dated March 30, 2011. (ii) Airbus Service Bulletin A300-57-143, Revision 2, dated July 10, 1989. Pages 1, 3, 4, 7, 10, 13, and 14 of this document are identified as Revision 2, dated July 10, 1989; pages 2 and 8 are identified as original, dated December 12, 1986; and pages 5, 6, 9, 11, 12, and 15 are identified as Revision March 19, 1987. (iii) Airbus Service Bulletin A300-57-6010, Revision 05, dated February 21, 2011. (iv) Airbus Service Bulletin A300-57-6011, Revision 2, dated July 10, 1989. Pages 1, 2, 5, 7, 8, 11, and 12 of this document are identified as Revision 2, dated July 10, 1989; pages 3, 4, and 13 are identified as Revision 1, dated March 19, 1987; and pages 6, 9, 10 are identified as original, dated December 17, 1986. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 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 August 24, 2016. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-21146 Filed 9-14-16; 8:45 am] BILLING CODE 4910-13-P
![63370 Federal Register / Vol. 81, No. 179 / Thursday, September 15, 2016 / Rules and Regulations
(j) Modification of Overhead Stowage (IBR) of the service information listed in this for cracking in the aft hinge brackets of
Compartments and Re-Identification of Part paragraph under 5 U.S.C. 552(a) and 1 CFR the outer shroud box that is located in
Number part 51. the outer wing box, and related
Within 4 months after the effective date of (2) You must use this service information
investigative and corrective actions if
this AD: Modify the overhead stowage as applicable to do the actions required by
this AD, unless this AD specifies otherwise. necessary. This new AD changes certain
compartments, in accordance with the compliance times and adds airplanes to
Accomplishment Instructions of the (i) ATR Service Bulletin ATR42–25–0180,
applicable service information identified in dated August 19, 2013. the applicability. This AD was
paragraphs (j)(1) through (j)(4) of this AD. (ii) ATR Service Bulletin ATR42–25–0185, prompted by reports of cracks in the aft
(1) For airplanes identified in ATR Service dated November 21, 2014. hinge brackets of the outer shroud box
Bulletin ATR42–25–0185, dated November (iii) ATR Service Bulletin ATR42–25–0186, that is located in the outer wing box,
21, 2014: ATR Service Bulletin ATR42–25– dated November 21, 2014. which were found during routine
0185, dated November 21, 2014. (iv) ATR Service Bulletin ATR72–25–1141, maintenance checks, and our
(2) For airplanes identified in ATR Service dated August 19, 2013.
subsequent determination that a change
Bulletin ATR42–25–0186, dated November (v) ATR Service Bulletin ATR72–25–1148,
dated November 21, 2014. in inspection compliance times is
21, 2014: ATR Service Bulletin ATR42–25–
(vi) ATR Service Bulletin ATR72–25–1149, needed. We are issuing this AD to detect
0186, dated November 21, 2014.
(3) For airplanes identified in ATR Service dated November 21, 2014. and correct cracking of the aft hinge
Bulletin ATR72–25–1148, dated November (3) For service information identified in brackets of the outer shroud box; such
21, 2014: ATR Service Bulletin ATR72–25– this AD, contact ATR—GIE Avions de cracking could affect the structural
1148, dated November 21, 2014. Transport Régional, 1, Allée Pierre Nadot, integrity of the airplane.
(4) For airplanes identified in ATR Service 31712 Blagnac Cedex, France; telephone +33 DATES: This AD becomes effective
Bulletin ATR72–25–1149, dated November (0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18;
October 20, 2016.
21, 2014: ATR Service Bulletin ATR72–25– email continued.airworthiness@atr.fr;
Internet http://www.aerochain.com.
The Director of the Federal Register
1149, dated November 21, 2014.
(4) You may view this service information approved the incorporation by reference
(k) Other FAA AD Provisions at the FAA, Transport Airplane Directorate, of certain publications listed in this AD
The following provisions also apply to this 1601 Lind Avenue SW., Renton, WA. For as of October 20, 2016.
AD: information on the availability of this ADDRESSES: For service information
(1) Alternative Methods of Compliance material at the FAA, call 425–227–1221. identified in this final rule, contact
(AMOCs): The Manager, International (5) You may view this service information Airbus SAS, Airworthiness Office—
Branch, ANM–116, Transport Airplane that is incorporated by reference at the
EAW, 1 Rond Point Maurice Bellonte,
Directorate, FAA, has the authority to National Archives and Records
approve AMOCs for this AD, if requested Administration (NARA). For information on 31707 Blagnac Cedex, France; telephone
using the procedures found in 14 CFR 39.19. the availability of this material at NARA, call +33 5 61 93 36 96; fax +33 5 61 93 44
In accordance with 14 CFR 39.19, send your 202–741–6030, or go to: http:// 51; email account.airworth-eas@
request to your principal inspector or local www.archives.gov/federal-register/cfr/ibr- airbus.com; Internet http://
Flight Standards District Office, as locations.html. www.airbus.com. You may view this
appropriate. If sending information directly referenced service information at the
Issued in Renton, Washington, on August
to the International Branch, send it to ATTN: FAA, Transport Airplane Directorate,
25, 2016.
Tom Rodriguez, Aerospace Engineer, 1601 Lind Avenue SW., Renton, WA.
International Branch, ANM–116, Transport John P. Piccola, Jr.,
Acting Manager, Transport Airplane For information on the availability of
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356; Directorate, Aircraft Certification Service. this material at the FAA, call 425–227–
telephone 425–227–1137; fax 425–227–1149. [FR Doc. 2016–21292 Filed 9–14–16; 8:45 am]
1221. It is also available on the Internet
Information may be emailed to: 9-ANM-116- at http://www.regulations.gov by
BILLING CODE 4910–13–P
AMOC-REQUESTS@faa.gov. Before using searching for and locating Docket No.
any approved AMOC, notify your appropriate FAA–2015–6550.
principal inspector, or lacking a principal
DEPARTMENT OF TRANSPORTATION Examining the AD Docket
inspector, the manager of the local flight
standards district office/certificate holding You may examine the AD docket on
Federal Aviation Administration
district office. the Internet at http://
(2) Contacting the Manufacturer: For any www.regulations.gov by searching for
requirement in this AD to obtain corrective 14 CFR Part 39
actions from a manufacturer, the action must
and locating Docket No. FAA–2015–
[Docket No. FAA–2015–6550; Directorate 6550; or in person at the Docket
be accomplished using a method approved Identifier 2013–NM–162–AD; Amendment
by the Manager, International Branch, ANM– Management Facility between 9 a.m.
39–18638; AD 2016–18–08]
116, Transport Airplane Directorate, FAA; or and 5 p.m., Monday through Friday,
EASA; or ATR—GIE Avions de Transport RIN 2120–AA64 except Federal holidays. The AD docket
Régional’s EASA DOA. If approved by the contains this AD, the regulatory
DOA, the approval must include the DOA- Airworthiness Directives; Airbus evaluation, any comments received, and
authorized signature. Airplanes other information. The address for the
(l) Related Information AGENCY: Federal Aviation Docket Office (telephone 800–647–5527)
Refer to Mandatory Continuing Administration (FAA), Department of is Docket Management Facility, U.S.
Airworthiness Information (MCAI) EASA Transportation (DOT). Department of Transportation, Docket
Airworthiness Directive 2015–0018, dated Operations, M–30, West Building
ACTION: Final rule.
February 5, 2015, for related information. Ground Floor, Room W12–140, 1200
This MCAI may be found in the AD docket SUMMARY: We are superseding New Jersey Avenue SE., Washington,
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on the Internet at http://www.regulations.gov Airworthiness Directive (AD) 90–11–05 DC 20590.
by searching for and locating Docket No.
for certain Airbus Model A300 B2–1C, FOR FURTHER INFORMATION CONTACT: Dan
FAA–2015–0077.
B2K–3C, B2–203, B4–2C, B4–103, and Rodina, Aerospace Engineer,
(m) Material Incorporated by Reference B4–203 airplanes and Model A300 B4– International Branch, ANM–116,
(1) The Director of the Federal Register 600 series airplanes. AD 90–11–05 Transport Airplane Directorate, FAA,
approved the incorporation by reference required repetitive detailed inspections 1601 Lind Avenue SW., Renton, WA
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![Federal Register / Vol. 81, No. 179 / Thursday, September 15, 2016 / Rules and Regulations 63371
98057–3356; telephone 425–227–2125; The results of these analyses led to a terminating actions provided in
fax 425–227–1149. change in the inspection thresholds and paragraph (j)(1) of the proposed AD, and
intervals in Flight Cycles (FC) and the specified in Airbus Service Bulletin
SUPPLEMENTARY INFORMATION:
introduction of Flight Hours (FH) limits. A300–57–6011, Revision 2, dated July
Discussion For the reasons described above, this
[EASA] AD retains the requirements of DGAC
10, 1989, on several of its airplanes.
We issued a notice of proposed France * * * [an airworthiness directive], We disagree with FedEx’s request. As
rulemaking (NPRM) to amend 14 CFR which is superseded, but requires those of the effective date of this AD,
part 39 to supersede AD 90–11–05, actions within the new thresholds and additional actions are required for
Amendment 39–6603 (89–NM–223–AD) intervals given by Airbus Service Bulletin airplanes on which the optional
(55 FR 20129, May 15, 1990) (‘‘AD 90– (SB) A300–57–0142 Revision 04 or A300–57– modification has been accomplished.
11–05’’). AD 90–11–05 applied to 6010 Revision 05, as applicable to aeroplane These airplanes will need to have a one-
certain Airbus Model A300 B2–1C, model.
Revision 1 of this [EASA] AD is issued to
time detailed visual inspection of the
B2K–3C, B2–203, B4–2C, B4–103, and forward and aft outer shroud box with
B4 203 airplanes and Model A300 B4– add model A300 B4–203 aeroplanes to the
applicability and compliance time tables. no cracking found, as required by
600 series airplanes. The NPRM This model is covered by Airbus SB A300– paragraph (j)(2) of this AD. We have not
published in the Federal Register on 57–0142, but was mistakenly omitted from changed this AD in this regard.
December 14, 2015 (80 FR 77279) (‘‘the the original [EASA] AD issue.
NPRM’’). The NPRM was prompted by Changes Made to This AD
a determination that a change to certain The corrective action for a hinge
bracket that is cracked or fractured is In paragraph (j)(2) of the proposed
compliance times is needed. The NPRM AD, we proposed to provide an optional
proposed to continue to require doing replacing the damaged hinge bracket
with a new bracket. method of compliance (i.e., a
repetitive detailed inspections for replacement and a one-time inspection)
cracking in the hinge brackets of the For airplanes on which a crack is
found in one half bracket or both half for actions specified in paragraph (g) of
forward and aft outer shroud boxes that the proposed AD. We also proposed to
are located in the outer wing box, and brackets, related investigative actions
include a general visual inspection for give credit in paragraph (k)(2) of the
related investigative and corrective proposed AD for replacements
actions if necessary. The NPRM also secondary damage (e.g., cracks, wear
damage, pitting, and gouging) in the accomplished before the effective date
proposed to change certain compliance of this AD using the same service
times and add airplanes to the following areas:
• The inner shroud-box forward information identified in paragraph
applicability. We are issuing this AD to (j)(2) of the AD:
detect and correct cracking of the aft attachments and the attachment
brackets at the inboard end. • Airbus Service Bulletin A300–57–
hinge brackets of the outer shroud box;
such cracking could affect the structural • The inner and outer shroud-box 143, dated December 17, 1986.
integrity of the airplane. structure, adjacent to the fractured • Airbus Service Bulletin A300–57–
The European Aviation Safety Agency bracket. 143, Revision 1, dated March 19, 1987.
(EASA), which is the Technical Agent • The top skin of the inboard flap. • Airbus Service Bulletin A300–57–
for the Member States of the European The corrective action for damage 6011, dated December 17, 1986.
Union, has issued EASA Airworthiness findings during the related investigative • Airbus Service Bulletin A300–57–
Directive 2013–0181R1, dated August action is repair using a method 6011, Revision 1, dated March 19, 1987.
20, 2013 (referred to after this as the approved by the Manager, International
Branch, ANM–116, Transport Airplane Since we cannot make this service
Mandatory Continuing Airworthiness information reasonably available, we
Information, or ‘‘the MCAI’’), to correct Directorate, FAA; or EASA; or Airbus’s
EASA Design Organization Approval have revised paragraph (j)(2) of the
an unsafe condition for certain Model proposed AD, removed redundant
A300 series airplanes and Model A300 (DOA).
The compliance time for related paragraph (k)(2) of the proposed AD
B4–600 series airplanes. The MCAI from this AD, and redesignated
states: investigative actions and corrective
actions is before further flight. paragraph (k)(1) and subsequent
In the past, aft hinge brackets of the outer You may examine the MCAI in the subparagraphs accordingly. We revised
wing box were found cracked. Fracture of a
AD docket on the Internet at http:// paragraph (j)(2) of this AD by removing
bracket would allow vertical movement of the references to the service information
the inner shroud box structure, which could www.regulations.gov by searching for
and locating Docket No. FAA–2015– and instead specified that operators
result in damage to the top skin of the must do the replacement using a
inboard flap. In addition, the loads carried by 6550.
the brackets will be transferred to the method approved by the Manager,
remaining supports, which may also crack Comments International Branch, ANM–116,
and cause extensive structural damage. We gave the public the opportunity to Transport Airplane Directorate, FAA; or
This condition, if not detected and participate in developing this AD. The EASA; or Airbus’s EASA Design
corrected, could affect the structural integrity Organization Approval (DOA).
following presents the comment
of the aeroplane.
To address this potential unsafe condition, received on the NPRM and the FAA’s Conclusion
DGAC [Direction Générale de l’Aviation response to the comment.
Civile] France issued * * * [an airworthiness We reviewed the available data,
Request To Exclude Certain Airplanes including the comment received, and
directive] (later revised) to require repetitive
inspections of the hinge bracket of the outer From the Applicability determined that air safety and the
box and, depending on findings, corrective FedEx requested that we exclude from public interest require adopting this AD
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action(s). the proposed applicability airplanes on as proposed except for minor editorial
Since that [DGAC] AD was issued, a fleet which the actions specified in Airbus changes. We have determined that these
survey and updated Fatigue and Damage minor changes:
Tolerance analysis were performed in order Service Bulletin A300–57–6011,
to substantiate the A300 Extended Service Revision 2, dated July 10, 1989, have • Are consistent with the intent that
Goal (ESG) and A300–600 Extended Service been accomplished. FedEx stated that it was proposed in the NPRM for
Goal (ESG2) exercise. has accomplished the optional correcting the unsafe condition; and
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![63372 Federal Register / Vol. 81, No. 179 / Thursday, September 15, 2016 / Rules and Regulations
• Do not add any additional burden • Airbus Service Bulletin A300–57– replacing the aft aluminum alloy
upon the public than was already 143, Revision 2, dated July 10, 1989, brackets on the outer shroud box with
proposed in the NPRM. which describes procedures for new steel brackets.
replacing the aft aluminum alloy This service information is reasonably
Related Service Information Under 1 brackets on the outer shroud box with
CFR Part 51 available because the interested parties
new steel brackets. have access to it through their normal
• Airbus Service Bulletin A300–57– course of business or by the means
Airbus has issued the following
6010, Revision 05, dated February 21, identified in the ADDRESSES section.
service information.
2011, which describes procedures for
• Airbus Service Bulletin A300–57– doing an inspection of the forward and Costs of Compliance
0142, Revision 04, dated March 30, aft hinge brackets on the outer shroud
2011, which describes procedures for box. We estimate that this AD affects 3
doing an inspection of the forward and • Airbus Service Bulletin A300–57– airplanes of U.S. registry.
aft hinge brackets on the outer shroud 6011, Revision 2, dated July 10, 1989, We estimate the following costs to
box. which describes procedures for comply with this AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspection ...................... 8 work-hours × $85 per hour = $680 per in- $0 $680 per inspection $2,040 per inspection
spection cycle. cycle. cycle.
We estimate the following costs to do be required based on the results of the determining the number of aircraft that
any necessary replacements that would inspection. We have no way of might need these replacements:
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Replacement .................................... 27 work-hours × $85 per hour = $2,295 ................................................... $25,650 $27,945
We have received no definitive data not have a substantial direct effect on PART 39—AIRWORTHINESS
that would enable us to provide cost the States, on the relationship between DIRECTIVES
estimates for the on-condition related the national government and the States,
investigative and corrective actions or on the distribution of power and ■ 1. The authority citation for part 39
specified in this AD. responsibilities among the various continues to read as follows:
Authority for This Rulemaking levels of government. Authority: 49 U.S.C. 106(g), 40113, 44701.
Title 49 of the United States Code For the reasons discussed above, I § 39.13 [Amended]
specifies the FAA’s authority to issue certify that this AD:
rules on aviation safety. Subtitle I, ■ 2. The FAA amends § 39.13 by
1. Is not a ‘‘significant regulatory
section 106, describes the authority of removing Airworthiness Directive (AD)
action’’ under Executive Order 12866;
the FAA Administrator. ‘‘Subtitle VII: 90–11–05, Amendment 39–6603 (89–
2. Is not a ‘‘significant rule’’ under the NM–223–AD) (55 FR 20129, May 15,
Aviation Programs,’’ describes in more
detail the scope of the Agency’s DOT Regulatory Policies and Procedures 1990), and adding the following new
authority. (44 FR 11034, February 26, 1979); AD:
We are issuing this rulemaking under 3. Will not affect intrastate aviation in 2016–18–08 Airbus: Amendment 39–18638.
the authority described in ‘‘Subtitle VII, Alaska; and Docket No. FAA–2015–6550; Directorate
Part A, Subpart III, Section 44701: 4. Will not have a significant
Identifier 2013–NM–162–AD.
General requirements.’’ Under that (a) Effective Date
economic impact, positive or negative,
section, Congress charges the FAA with
on a substantial number of small entities This AD becomes effective October 20,
promoting safe flight of civil aircraft in
under the criteria of the Regulatory 2016.
air commerce by prescribing regulations
for practices, methods, and procedures Flexibility Act. (b) Affected ADs
the Administrator finds necessary for List of Subjects in 14 CFR Part 39 This AD replaces AD 90–11–05,
safety in air commerce. This regulation Amendment 39–6603 (89–NM–223–AD) (55
is within the scope of that authority Air transportation, Aircraft, Aviation FR 20129, May 15, 1990).
because it addresses an unsafe condition safety, Incorporation by reference, (c) Applicability
that is likely to exist or develop on Safety.
This AD applies to Airbus Model A300 B2–
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products identified in this rulemaking 1C, B2K–3C, B2–203, B4–2C, B4–103, and
action. Adoption of the Amendment
B4–203 airplanes; Model A300 B4–601, B4–
Regulatory Findings Accordingly, under the authority 603, B4–620, and B4–622 airplanes; and
delegated to me by the Administrator, Model A300 B4–605R airplanes; certificated
We determined that this AD will not in any category; except airplanes on which
have federalism implications under the FAA amends 14 CFR part 39 as
Airbus Modification 6661 has been embodied
Executive Order 13132. This AD will follows: during production.
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![63374 Federal Register / Vol. 81, No. 179 / Thursday, September 15, 2016 / Rules and Regulations
(2) You must use this service information AW109SP helicopters. This AD requires notice of proposed rulemaking (NPRM),
as applicable to do the actions required by visually inspecting the tail rotor drive which proposed to amend 14 CFR part
this AD, unless this AD specifies otherwise. shaft assembly (drive shaft) for a crack. 39 by adding an AD that would apply
(i) Airbus Service Bulletin A300–57–0142,
This AD was prompted by the discovery to Agusta S.p.A. Model A109A, A109A
Revision 04, dated March 30, 2011.
(ii) Airbus Service Bulletin A300–57–143, of three cracks on the drive shaft of a II, A109C, A109E, A109K2, A109S, and
Revision 2, dated July 10, 1989. Pages 1, 3, Model A109S helicopter. The actions of AW109SP helicopters with a drive shaft
4, 7, 10, 13, and 14 of this document are this AD are intended to detect a crack part number (P/N) 109–8412–02–1 or
identified as Revision 2, dated July 10, 1989; on the drive shaft to prevent failure of 109–8412–02–3 installed. The NPRM
pages 2 and 8 are identified as original, dated the driveshaft, failure of the tail rotor, proposed to require visually inspecting
December 12, 1986; and pages 5, 6, 9, 11, 12, and subsequent loss of helicopter the drive shaft for a crack. The proposed
and 15 are identified as Revision March 19, control. requirements were intended to detect a
1987. crack on the drive shaft to prevent
(iii) Airbus Service Bulletin A300–57– DATES: This AD is effective October 20,
6010, Revision 05, dated February 21, 2011. 2016. failure of the driveshaft, failure of the
(iv) Airbus Service Bulletin A300–57– The Director of the Federal Register tail rotor, and subsequent loss of
6011, Revision 2, dated July 10, 1989. Pages approved the incorporation by reference helicopter control.
1, 2, 5, 7, 8, 11, and 12 of this document are of certain documents listed in this AD The NPRM was prompted by AD No.
identified as Revision 2, dated July 10, 1989; as of October 20, 2016. 2015–0054, dated March 27, 2015,
pages 3, 4, and 13 are identified as Revision issued by EASA, which is the Technical
1, dated March 19, 1987; and pages 6, 9, 10 ADDRESSES: For service information
Agent for the Member States of the
are identified as original, dated December 17, identified in this final rule, contact
European Union, to correct an unsafe
1986. AgustaWestland, Product Support
condition for the Model A109A with
(3) For service information identified in Engineering, Via del Gregge, 100, 21015
this AD, contact Airbus SAS, Airworthiness retrofit kit P/N 109–0820–27–101
Lonate Pozzolo (VA) Italy, ATTN:
Office—EAW, 1 Rond Point Maurice installed, and Model A109A II, A109C,
Maurizio D’Angelo; telephone 39–0331–
Bellonte, 31707 Blagnac Cedex, France; A109E, A109K2, A109LUH, A109S, and
664757; fax 39–0331–664680; or at
telephone +33 5 61 93 36 96; fax +33 5 61 AW109SP helicopters.
93 44 51; email account.airworth-eas@
http://www.agustawestland.com/ EASA advises that during scheduled
airbus.com; Internet http://www.airbus.com. technical-bulletins. You may review the maintenance on a Model A109S
(4) You may view this service information referenced service information at the helicopter, three cracks were found on
at the FAA, Transport Airplane Directorate, FAA, Office of the Regional Counsel, the drive shaft. An investigation could
1601 Lind Avenue SW., Renton, WA. For Southwest Region, 10101 Hillwood not determine the cause of the cracking
information on the availability of this Pkwy, Room 6N–321, Fort Worth, TX
material at the FAA, call 425–227–1221. but concluded it could not have been
76177. It is also available on the Internet caused by fatigue. This condition, if not
(5) You may view this service information at http://www.regulations.gov by
that is incorporated by reference at the detected and corrected, could lead to
searching for and locating Docket No. tail rotor failure, possibly resulting in
National Archives and Records
Administration (NARA). For information on FAA–2015–3781. loss of helicopter control, EASA
the availability of this material at NARA, call Examining the AD Docket advises. EASA AD No. 2015–0054
202–741–6030, or go to: http:// consequently requires a one-time
www.archives.gov/federal-register/cfr/ibr- You may examine the AD docket on
the Internet at http:// inspection of the drive shaft, and
locations.html.
www.regulations.gov by searching for replacing the drive shaft if cracks are
Issued in Renton, Washington, on August found.
24, 2016. and locating Docket No. FAA–2015–
John P. Piccola, Jr.,
3781; or in person at the Docket Comments
Operations Office between 9 a.m. and 5 We gave the public the opportunity to
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
p.m., Monday through Friday, except participate in developing this AD, but
Federal holidays. The AD docket we received no comments on the NPRM
[FR Doc. 2016–21146 Filed 9–14–16; 8:45 am]
contains this AD, the European Aviation (81 FR 15171, March 22, 2016).
BILLING CODE 4910–13–P
Safety Agency (EASA) AD, any
incorporated-by-reference service FAA’s Determination
information, the economic evaluation, These helicopters have been approved
DEPARTMENT OF TRANSPORTATION
any comments received, and other by the aviation authority of Italy and are
Federal Aviation Administration information. The street address for the approved for operation in the United
Docket Operations Office (phone: 800– States. Pursuant to our bilateral
14 CFR Part 39 647–5527) is U.S. Department of agreement with Italy, EASA, its
Transportation, Docket Operations technical representative, has notified us
[Docket No. FAA–2015–3781; Directorate Office, M–30, West Building Ground
Identifier 2015–SW–048–AD; Amendment of the unsafe condition described in the
Floor, Room W12–140, 1200 New Jersey EASA AD. We are issuing this AD
39–18649; AD 2016–18–18]
Avenue SE., Washington, DC 20590. because we evaluated all information
RIN 2120–AA64 FOR FURTHER INFORMATION CONTACT: provided by EASA and determined the
Martin R. Crane, Aviation Safety unsafe condition exists and is likely to
Airworthiness Directives; Agusta Engineer, Safety Management Group, exist or develop on other helicopters of
S.p.A. Helicopters Rotorcraft Directorate, FAA, 10101 these same type designs and that air
AGENCY: Federal Aviation Hillwood Pkwy, Fort Worth, TX 76177; safety and the public interest require
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Administration (FAA), DOT. telephone (817) 222–5110; email adopting the AD requirements as
ACTION: Final rule. martin.r.crane@faa.gov. proposed.
SUPPLEMENTARY INFORMATION:
SUMMARY: We are adopting a new Interim Action
airworthiness directive (AD) for Agusta Discussion We consider this AD to be an interim
S.p.A. (Agusta) Model A109A, A109A II, On March 22, 2016, at 81 FR 15171, action. The design approval holder has
A109C, A109E, A109K2, A109S, and the Federal Register published our not determined the cause of the unsafe
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Document Created: 2018-02-09 13:18:31
Document Modified: 2018-02-09 13:18:31
| 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 October 20, 2016. | |
| Contact | Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. | |
| FR Citation | 81 FR 63370 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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