81 FR 21255 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 69 (April 11, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 69 (April 11, 2016)
| Page Range | 21255-21258 | |
| FR Document | 2016-07570 |
[Federal Register Volume 81, Number 69 (Monday, April 11, 2016)] [Rules and Regulations] [Pages 21255-21258] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-07570] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-4817; Directorate Identifier 2014-NM-115-AD; Amendment 39-18465; AD 2016-07-20] 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) 95-18-08 for all Airbus Model A300-600 series airplanes. AD 95-18-08 required repetitive inspections to detect cracks in the bottom skin of the wing in the area of the cut-out for the pylon rear attachment fitting, and repair if necessary. This new AD, for certain [[Page 21256]] airplanes, reduces the compliance times for the inspections. This AD was prompted by a report that updated fatigue and damage tolerance analyses and a fleet survey found that certain inspection thresholds and intervals must be reduced to allow more timely findings of cracking. We are issuing this AD to detect and correct fatigue-related cracking in the bottom skin of the wing in the area of the cut-out for the pylon rear attachment fitting, which could result in reduced structural integrity of the wing. DATES: This AD becomes effective May 16, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 16, 2016. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of October 16, 1995 (60 FR 47677, September 14, 1995). ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-4817; 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 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- 4817. FOR FURTHER INFORMATION 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. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 95-18-08, Amendment 39-9355 (60 FR 47677, September 14, 1995) (``AD 95-18-08''). AD 95-18-08 applied to all Airbus Model A300-600 series airplanes (which includes Airbus Model A300 C4-605R Variant F airplanes), Model A300 B4-622 airplanes, and Model A300 F4-622R airplanes that were added to the U.S. Type Certificate Data Sheet since issuance of AD 95-18-08. The NPRM published in the Federal Register on November 19, 2015 (80 FR 72395) (``the NPRM'' or ``the proposed AD''). The NPRM was prompted by a report that updated fatigue and damage tolerance analyses and a fleet survey found that certain inspection thresholds and intervals must be reduced to allow more timely findings of cracking. The NPRM proposed to continue to require repetitive inspections to detect cracks in the bottom skin of the wing in the area of the cut-out for the pylon rear attachment fitting, and repair if necessary. The NPRM also proposed, for certain airplanes, reduce the compliance times for the inspections. We are issuing this AD to detect and correct such fatigue-related cracking in the bottom skin of the wing in the area of the cut-out for the pylon rear attachment fitting, which could result in reduced structural integrity of the wing. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0119, dated May 13, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition on all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). The MCAI states: Full-scale fatigue tests carried out on the A300-600 test specimen by Airbus revealed crack initiation in the bottom skin adjacent to the aft pylon attachment fitting. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. To address this unsafe condition, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 94- 069-158(B) (http://ad.easa.europa.eu/blob/1994069158tb_superseded.pdf/AD_F-1994-069-158_2) [which corresponds to FAA AD 95-18-08, Amendment 39-9355 (60 FR 47677, September 14, 1995)] to require repetitive detailed visual inspections (DVI) of the wing bottom skin in the area of the cut-out for the pylon rear attachment fitting on Left Hand (LH) and Right Hand (RH) wings [to detect cracks, and repair if necessary]. Since that [DGAC] AD was issued, a fleet survey and updated Fatigue and Damage Tolerance analyses have been performed in order to substantiate the second A300-600 Extended Service Goal (ESG2) exercise. As a result, it was revealed that the inspection threshold and interval must be reduced to allow timely detection of cracks and the accomplishment of an applicable corrective action. Prompted by these findings, Airbus issued Revision 07 of Service Bulletin (SB) A300-57-6028. For the reasons described above, this [EASA] AD retains the requirements of DGAC France AD 94-069-158(B), which is superseded, but reduces the inspection thresholds and intervals [e.g., compliance times]. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-4817-0002. Comment The following presents the comment received on the NPRM and the FAA's response to the comment. Statement on Fleet Activity FedEx Express (FedEx) stated that the NPRM will affect 71 Model A300 airplanes in its fleet. FedEx stated that 42 of its Model A300-F4 airplanes have not reached the inspection threshold, and it is currently accomplishing repetitive actions on 15 of its 29 Model A300- B4 airplanes. FedEx stated that it will adjust its inspection actions to comply with the actions specified in the NPRM. We acknowledge FedEx's comment. No change to this AD is necessary. 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 Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 We reviewed Airbus Service Bulletin A300-57-6028, Revision 07, dated June 6, 2011. The service information describes procedures for inspections to detect cracks in the bottom skin of the wing in the area of the cut-out for the pylon rear attachment fitting, and repair. 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. [[Page 21257]] Costs of Compliance We estimate that this AD affects 124 airplanes of U.S. registry. The actions required by AD 95-18-08, and retained in this AD take about 6 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 95-18-08 is $510 per product. In addition, we estimate that any necessary follow-on actions would take about 15 work-hours and require parts costing $10,000, for a cost of $11,275 per product. We have no way of determining the number of aircraft that might need these actions. The new requirements of this AD add no additional economic burden. 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-2015-4817; 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) 95-18-08, Amendment 39-9355 (60 FR 47677, September 14, 1995), and adding the following new AD: 2016-07-20 Airbus: Amendment 39-18465. Docket No. FAA-2015-4817; Directorate Identifier 2014-NM-115-AD. (a) Effective Date This AD becomes effective May 16, 2016. (b) Affected ADs This AD replaces AD 95-18-08, Amendment 39-9355 (60 FR 47677, September 14, 1995) (``AD 95-18-08''). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes. (2) Airbus Model A300 B4-605R and B4-622R airplanes. (3) Airbus Model A300 F4-605R and F4-622R airplanes. (4) Airbus Model A300 C4-605R Variant F airplanes. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a report that updated fatigue and damage tolerance analyses and a fleet survey found that certain inspection thresholds and intervals must be reduced to allow more timely findings of cracking. We are issuing this AD to detect and correct such fatigue-related cracking in the bottom skin of the wing in the area of the cut-out for the pylon rear attachment fitting, which could result in reduced structural integrity of the wing. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection and Corrective Action with Additional Repair Information This paragraph restates the requirements of paragraph (a) of AD 95-18-08, with additional repair contact information. Prior to the accumulation of 24,000 total flight cycles since date of manufacture of the airplane, or within 750 flight cycles after October 16, 1995 (the effective date of AD 95-18-08), whichever occurs later, perform a detailed visual inspection to detect cracks in the bottom skin of the wing in the area of the cut-out for the pylon rear attachment fitting, in accordance with Airbus Service Bulletin A300-57-6028, Revision 3, dated September 13, 1994. Repeat the inspection thereafter at intervals not to exceed 9,000 flight cycles. If any crack is detected, prior to further flight, repair the wing bottom skin in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, or 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). Accomplishing any inspection required by paragraph (h) of this AD terminates the inspections required by this paragraph. (h) New Requirement of This AD: Revised Inspection Thresholds and Intervals Within the applicable compliance times required in paragraphs (h)(1) and (h)(2) of this AD, do a detailed visual inspection of the wing bottom skin in the area of the cut-out for the pylon rear attachment fitting on left-hand and right-hand wings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6028, Revision 07, dated June 6, 2011. Repeat the inspections thereafter at the applicable intervals required in paragraphs (h)(3) and (h)(4) of this AD. Accomplishing any inspection required by this paragraph terminates the inspections required by paragraph (g) of this AD. (1) For ``normal range operations'' airplanes having an average flight time of 1.5 flight hours or more: Do the inspection at the applicable time required in paragraphs (h)(1)(i) and (h)(1)(ii) of this AD. (i) For Model A300 F4-605R and F4-622R airplanes: Do the inspection at the later of the times specified in paragraphs (h)(1)(i)(A) and (h)(1)(i)(B) of this AD. [[Page 21258]] (A) Within 24,000 flight cycles or 51,800 flight hours after first flight of the airplane, whichever occurs first. (B) Within 2,000 flight cycles or 4,300 flight hours after the effective date of this AD, whichever occurs first. (ii) For Model A300 B4-600, B4-600R, and Model A300 C4-605R Variant F airplanes: Do the inspection at the later of the times specified in paragraphs (h)(1)(ii)(A) and (h)(1)(ii)(B) of this AD. (A) Within 19,100 flight cycles or 41,200 flight hours after first flight of the airplane, whichever occurs first. (B) Within 1,500 flight cycles or 3,200 flight hours after the effective date of this AD, whichever occurs first. (2) For ``short range operations'' airplanes having an average flight time of less than 1.5 flight hours: Do the inspection at the applicable time required in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD. (i) For Model A300 F4-605R and F4-622R airplanes: Do the inspection at the later of the times specified in paragraphs (h)(2)(i)(A) and (h)(2)(i)(B) of this AD. (A) Within 25,900 flight cycles or 38,800 flight hours after first flight of the airplane, whichever occurs first. (B) Within 2,100 flight cycles or 3,200 flight hours after the effective date of this AD, whichever occurs first. (ii) For Model A300 B4-600, B4-600R, and Model A300 C4-605R Variant F airplanes: Do the inspection at the later of the times specified in paragraphs (h)(2)(ii)(A) and (h)(2)(ii)(B) of this AD. (A) Within 20,600 flight cycles or 30,900 flight hours after first flight of the airplane, whichever occurs first. (B) Within 1,600 flight cycles or 2,400 flight hours after the effective date of this AD, whichever occurs first. (3) For ``normal range operations'' airplanes having an average flight time of 1.5 flight hours or more: Repeat the inspection at the applicable time required in paragraphs (h)(3)(i) and (h)(3)(ii) of this AD. (i) For Model A300 F4-605R and F4-622R airplanes: Repeat the inspection thereafter at intervals not to exceed 9,000 flight cycles or 19,400 flight hours, whichever occurs first. (ii) For Model A300 B4-600, B4-600R, and Model A300 C4-605R Variant F airplanes: Repeat the inspection thereafter at intervals not to exceed 7,100 flight cycles or 15,300 flight hours, whichever occurs first. (4) For ``short range operations'' airplanes having an average flight time of less than 1.5 flight hours: Repeat the inspection at the applicable time required in paragraphs (h)(4)(i) and (h)(4)(ii) of this AD. (i) For Model A300 F4-605R and F4-622R airplanes: Repeat the inspection thereafter at intervals not to exceed 9,700 flight cycles or 14,500 flight hours, whichever occurs first. (ii) For Model A300 B4-600, B4-600R, and Model A300 C4-605R Variant F airplanes: Repeat the inspection thereafter at intervals not to exceed 7,600 flight cycles or 11,500 flight hours, whichever occurs first. (i) Definition of Average Flight Time for Paragraph (h) of This AD For the purpose of paragraph (h) of this AD, the Average Flight Time must be established as follows: (1) For the initial inspection, the average flight time is the total accumulated flight hours, counted from take-off to touch-down, divided by the total accumulated flight cycles at the effective date of this AD. (2) For the first repeated inspection interval, the average flight time is the total accumulated flight hours divided by the total accumulated flight cycles at the time of the inspection threshold. (3) For all inspection intervals onwards, the average flight time is the flight hours divided by the flight cycles accumulated between the last two inspections. (j) New Requirement of This AD: Corrective Action for Any Cracking Found If any crack is found during any inspection required by paragraph (h) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. Accomplishing a repair does not constitute terminating action for the repetitive inspections required by paragraph (h) of this AD. (k) Credit for Previous Actions This paragraph provides credit for inspections required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using any of the service information identified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD, which are not incorporated by reference in this AD. (1) Airbus Service Bulletin A300-57-6028, Revision 04, dated October 25, 1999. (2) Airbus Service Bulletin A300-57-6028, Revision 05, dated January 11, 2002. (3) Airbus Service Bulletin A300-57-6028, Revision 06, dated May 17, 2006. (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]. (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 95-18-08, are approved as AMOCs for the corresponding provisions of paragraph (g) of this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the 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) European Aviation Safety Agency Airworthiness Directive 2014- 0119, dated May 13, 2014, 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-2015-4817. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (n)(5) and (n)(6) 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. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on May 16, 2016. (i) Airbus Service Bulletin A300-57-6028, Revision 07, dated June 6, 2011. (ii) Reserved. (4) The following service information was approved for IBR on October 16, 1995 (60 FR 47677, September 14, 1995). (i) Airbus Service Bulletin A300-57-6028, Revision 3, dated September 13, 1994. Pages 1 through 6 of this service bulletin indicate Revision 3 and are dated September 13, 1994; pages 7 through 9 indicate Revision 2 and are dated February 22, 1994. (ii) Reserved. (5) 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. (6) 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. (7) 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 March 24, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-07570 Filed 4-8-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 21255
PART 39—AIRWORTHINESS Bulletin MD80–57A244, dated March 3, 5224; fax: 562–627–5210; email:
DIRECTIVES 2016, refers to total flight cycles ‘‘as of the haytham.alaidy@faa.gov.
original issue date of this service bulletin.’’
This AD, however, applies to the airplanes (k) Material Incorporated by Reference
■ 1. The authority citation for part 39
with the specified total flight cycles as of the (1) The Director of the Federal Register
continues to read as follows:
effective date of this AD. approved the incorporation by reference
Authority: 49 U.S.C. 106(g), 40113, 44701. (3) If any crack is found during any (IBR) of the service information listed in this
inspection required by this AD, and Boeing paragraph under 5 U.S.C. 552(a) and 1 CFR
§ 39.13 [Amended] part 51.
Alert Service Bulletin MD80–57A244, dated
■ 2. The FAA amends § 39.13 by adding March 3, 2016, specifies to contact Boeing for (2) You must use this service information
the following new airworthiness appropriate action, and specifies that action as applicable to do the actions required by
directive (AD): as ‘‘RC’’ (Required for Compliance): Before this AD, unless the AD specifies otherwise.
further flight, repair using a method (i) Boeing Alert Service Bulletin MD80–
2016–07–28 The Boeing Company: approved in accordance with the procedures 57A244, dated March 3, 2016.
Amendment 39–18473; Docket No. specified in paragraph (i) of this AD. (ii) Reserved.
FAA–2016–5458; Directorate Identifier (3) For Boeing service information
2016–NM–027–AD. (i) Alternative Methods of Compliance identified in this AD, contact Boeing
(AMOCs) Commercial Airplanes, Attention: Data &
(a) Effective Date
(1) The Manager, Los Angeles Aircraft Services Management, 3855 Lakewood
This AD is effective April 26, 2016. Certification Office (ACO), FAA, has the Boulevard, MC D800–0019, Long Beach, CA
(b) Affected ADs authority to approve AMOCs for this AD, if 90846–0001; telephone 206–544–5000,
requested using the procedures found in 14 extension 2; fax 206–766–5683; Internet
None.
CFR 39.19. In accordance with 14 CFR 39.19, https://www.myboeingfleet.com.
(c) Applicability send your request to your principal inspector (4) You may view this referenced service
This AD applies to all The Boeing or local Flight Standards District Office, as information at the FAA, Transport Airplane
Company Model DC–9–81 (MD–81), DC–9– appropriate. If sending information directly Directorate, 1601 Lind Avenue SW., Renton,
82 (MD–82), DC–9–83 (MD–83), and DC–9– to the manager of the ACO, send it to the WA. For information on the availability of
87 (MD–87) airplanes, and Model MD–88 attention of the person identified in this material at the FAA, call 425–227–1221.
airplanes, certificated in any category. paragraph (j) of this AD. Information may be (5) You may view this service information
emailed to: 9-ANM-LAACO-AMOC- that is incorporated by reference at the
(d) Subject Requests@faa.gov. National Archives and Records
Air Transport Association (ATA) of (2) Before using any approved AMOC, Administration (NARA). For information on
America Code 57, Wings. notify your appropriate principal inspector, the availability of this material at NARA, call
or lacking a principal inspector, the manager 202–741–6030, or go to: http://
(e) Unsafe Condition of the local flight standards district office/ www.archives.gov/federal-register/cfr/ibr-
This AD was prompted by reports of certificate holding district office. locations.html.
cracking at certain stringers, associated end (3) An AMOC that provides an acceptable
Issued in Renton, Washington, on March
fittings, and skins in the center wing fuel level of safety may be used for any repair,
30, 2016.
tank where the stringers meet the end modification, or alteration required by this
AD if it is approved by the Boeing Victor Wicklund,
fittings. We are issuing this AD to detect and
correct cracking in the center wing lower Commercial Airplanes Organization Acting Manager, Transport Airplane
skin. Such cracking could cause structural Designation Authorization (ODA) that has Directorate, Aircraft Certification Service.
failure of the wings. been authorized by the Manager, Los Angeles [FR Doc. 2016–07842 Filed 4–8–16; 8:45 am]
ACO, to make those findings. To be BILLING CODE 4910–13–P
(f) Compliance approved, the repair method, modification
Comply with this AD within the deviation, or alteration deviation must meet
compliance times specified, unless already the certification basis of the airplane, and the
DEPARTMENT OF TRANSPORTATION
done. approval must specifically refer to this AD.
(4) Except as required by paragraph (h)(3)
(g) Inspection Federal Aviation Administration
of this AD: For service information that
Except as required by paragraph (h)(1) and contains steps that are labeled as Required
(h)(2) of this AD, at the applicable time for Compliance (RC), the provisions of 14 CFR Part 39
specified in paragraph 1.E., ‘‘Compliance,’’ of paragraphs (i)(4)(i) and (i)(4)(ii) of this AD [Docket No. FAA–2015–4817; Directorate
Boeing Alert Service Bulletin MD80–57A244, apply. Identifier 2014–NM–115–AD; Amendment
dated March 3, 2016: Do an eddy current (i) The steps labeled as RC, including 39–18465; AD 2016–07–20]
high frequency (ETHF) inspection for any substeps under an RC step and any figures
cracking in the left and right side center wing identified in an RC step, must be done to RIN 2120–AA64
lower skin, and do all applicable corrective comply with the AD. An AMOC is required
actions; except as required by paragraph for any deviations to RC steps, including Airworthiness Directives; Airbus
(h)(3) of this AD. Do all applicable corrective substeps and identified figures. Airplanes
actions before further flight. Repeat the (ii) Steps not labeled as RC may be
inspection thereafter at the intervals deviated from using accepted methods in AGENCY: Federal Aviation
specified in paragraph 1.E., ‘‘Compliance,’’ of accordance with the operator’s maintenance Administration (FAA), Department of
Boeing Alert Service Bulletin MD80–57A244, or inspection program without obtaining Transportation (DOT).
dated March 3, 2016. approval of an AMOC, provided the RC steps, ACTION: Final rule.
including substeps and identified figures, can
(h) Exception to the Service Information still be done as specified, and the airplane SUMMARY: We are superseding
(1) Where Boeing Alert Service Bulletin can be put back in an airworthy condition. Airworthiness Directive (AD) 95–18–08
jstallworth on DSK7TPTVN1PROD with RULES
MD80–57A244, dated March 3, 2016, for all Airbus Model A300–600 series
specifies a compliance time ‘‘after the (j) Related Information
airplanes. AD 95–18–08 required
original issue date of this service bulletin,’’ For more information about this AD,
this AD requires compliance within the contact Haytham Alaidy, Aerospace repetitive inspections to detect cracks in
specified compliance time after the effective Engineer, Airframe Branch, ANM–120L, the bottom skin of the wing in the area
date of this AD. FAA, Los Angeles Aircraft Certification of the cut-out for the pylon rear
(2) The Condition column of paragraph Office (ACO), 3960 Paramount Boulevard, attachment fitting, and repair if
1.E., ‘‘Compliance,’’ of Boeing Alert Service Lakewood, CA 90712–4137; phone: 562–627– necessary. This new AD, for certain
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airplanes, reduces the compliance times AD 95–18–08 applied to all Airbus threshold and interval must be reduced to
for the inspections. This AD was Model A300–600 series airplanes allow timely detection of cracks and the
prompted by a report that updated (which includes Airbus Model A300 accomplishment of an applicable corrective
fatigue and damage tolerance analyses C4–605R Variant F airplanes), Model action. Prompted by these findings, Airbus
issued Revision 07 of Service Bulletin (SB)
and a fleet survey found that certain A300 B4–622 airplanes, and Model A300–57–6028.
inspection thresholds and intervals A300 F4–622R airplanes that were For the reasons described above, this
must be reduced to allow more timely added to the U.S. Type Certificate Data [EASA] AD retains the requirements of DGAC
findings of cracking. We are issuing this Sheet since issuance of AD 95–18–08. France AD 94–069–158(B), which is
AD to detect and correct fatigue-related The NPRM published in the Federal superseded, but reduces the inspection
cracking in the bottom skin of the wing Register on November 19, 2015 (80 FR thresholds and intervals [e.g., compliance
in the area of the cut-out for the pylon 72395) (‘‘the NPRM’’ or ‘‘the proposed times].
rear attachment fitting, which could AD’’). The NPRM was prompted by a
result in reduced structural integrity of report that updated fatigue and damage You may examine the MCAI in the
the wing. tolerance analyses and a fleet survey AD docket on the Internet at http://
DATES: This AD becomes effective May found that certain inspection thresholds www.regulations.gov/
16, 2016. and intervals must be reduced to allow #!documentDetail;D=FAA-2015-4817-
The Director of the Federal Register more timely findings of cracking. The 0002.
approved the incorporation by reference NPRM proposed to continue to require Comment
of a certain publication listed in this AD repetitive inspections to detect cracks in
as of May 16, 2016. the bottom skin of the wing in the area The following presents the comment
The Director of the Federal Register of the cut-out for the pylon rear received on the NPRM and the FAA’s
approved the incorporation by reference attachment fitting, and repair if response to the comment.
of a certain other publication listed in necessary. The NPRM also proposed, for Statement on Fleet Activity
this AD as of October 16, 1995 (60 FR certain airplanes, reduce the compliance
47677, September 14, 1995). times for the inspections. We are issuing FedEx Express (FedEx) stated that the
ADDRESSES: You may examine the AD this AD to detect and correct such NPRM will affect 71 Model A300
docket on the Internet at http:// fatigue-related cracking in the bottom airplanes in its fleet. FedEx stated that
www.regulations.gov/ skin of the wing in the area of the cut- 42 of its Model A300–F4 airplanes have
#!docketDetail;D=FAA-2015-4817; or in out for the pylon rear attachment fitting, not reached the inspection threshold,
person at the Docket Management which could result in reduced structural and it is currently accomplishing
Facility, U.S. Department of integrity of the wing. repetitive actions on 15 of its 29 Model
Transportation, Docket Operations, M– The European Aviation Safety Agency A300–B4 airplanes. FedEx stated that it
30, West Building Ground Floor, Room (EASA), which is the Technical Agent will adjust its inspection actions to
W12–140, 1200 New Jersey Avenue SE., for the Member States of the European comply with the actions specified in the
Washington, DC. Union, has issued EASA Airworthiness NPRM.
For service information identified in Directive 2014–0119, dated May 13, We acknowledge FedEx’s comment.
this final rule, contact Airbus SAS, 2014 (referred to after this as the No change to this AD is necessary.
Airworthiness Office—EAW, 1 Rond Mandatory Continuing Airworthiness
Conclusion
Point Maurice Bellonte, 31707 Blagnac Information, or ‘‘the MCAI’’), to correct
Cedex, France; telephone +33 5 61 93 36 an unsafe condition on all Airbus Model We reviewed the available data,
96; fax +33 5 61 93 44 51; email A300 B4–600, B4–600R, and F4–600R including the comment received, and
account.airworth-eas@airbus.com; series airplanes, and Model A300 C4– determined that air safety and the
Internet http://www.airbus.com. You 605R Variant F airplanes (collectively public interest require adopting this AD
may view this referenced service called Model A300–600 series as proposed except for minor editorial
information at the FAA, Transport airplanes). The MCAI states: changes. We have determined that these
Airplane Directorate, 1601 Lind Avenue Full-scale fatigue tests carried out on the minor changes:
SW., Renton, WA. For information on A300–600 test specimen by Airbus revealed • Are consistent with the intent that
the availability of this material at the crack initiation in the bottom skin adjacent was proposed in the NPRM for
FAA, call 425–227–1221. It is also to the aft pylon attachment fitting. correcting the unsafe condition; and
This condition, if not detected and
available on the Internet at http://
corrected, could affect the structural integrity
• Do not add any additional burden
www.regulations.gov by searching for upon the public than was already
of the aeroplane.
and locating Docket No. FAA–2015– To address this unsafe condition, DGAC proposed in the NPRM.
4817. [Direction Générale de l’Aviation Civile]
France issued AD 94–069–158(B) (http://
Related Service Information Under 1
FOR FURTHER INFORMATION CONTACT: Dan
ad.easa.europa.eu/blob/1994069158tb_ CFR Part 51
Rodina, Aerospace Engineer,
International Branch, ANM–116, superseded.pdf/AD_F-1994-069-158_2) We reviewed Airbus Service Bulletin
[which corresponds to FAA AD 95–18–08,
Transport Airplane Directorate, FAA, Amendment 39–9355 (60 FR 47677,
A300–57–6028, Revision 07, dated June
1601 Lind Avenue SW., Renton, WA September 14, 1995)] to require repetitive 6, 2011. The service information
98057–3356; telephone 425–227–2125; detailed visual inspections (DVI) of the wing describes procedures for inspections to
fax 425–227–1149. bottom skin in the area of the cut-out for the detect cracks in the bottom skin of the
SUPPLEMENTARY INFORMATION: pylon rear attachment fitting on Left Hand wing in the area of the cut-out for the
jstallworth on DSK7TPTVN1PROD with RULES
(LH) and Right Hand (RH) wings [to detect pylon rear attachment fitting, and
Discussion cracks, and repair if necessary]. repair. This service information is
We issued a notice of proposed Since that [DGAC] AD was issued, a fleet reasonably available because the
survey and updated Fatigue and Damage
rulemaking (NPRM) to amend 14 CFR Tolerance analyses have been performed in interested parties have access to it
part 39 to supersede AD 95–18–08, order to substantiate the second A300–600 through their normal course of business
Amendment 39–9355 (60 FR 47677, Extended Service Goal (ESG2) exercise. As a or by the means identified in the
September 14, 1995) (‘‘AD 95–18–08’’). result, it was revealed that the inspection ADDRESSES section.
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![Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 21257
Costs of Compliance Examining the AD Docket (e) Reason
We estimate that this AD affects 124 This AD was prompted by a report that
You may examine the AD docket on updated fatigue and damage tolerance
airplanes of U.S. registry. the Internet at http://
The actions required by AD 95–18–08, analyses and a fleet survey found that certain
www.regulations.gov/ inspection thresholds and intervals must be
and retained in this AD take about 6
#!docketDetail;D=FAA-2015-4817; or in reduced to allow more timely findings of
work-hours per product, at an average
person at the Docket Management cracking. We are issuing this AD to detect
labor rate of $85 per work-hour. Based and correct such fatigue-related cracking in
Facility between 9 a.m. and 5 p.m.,
on these figures, the estimated cost of the bottom skin of the wing in the area of the
Monday through Friday, except Federal
the actions that were required by AD cut-out for the pylon rear attachment fitting,
holidays. The AD docket contains this
95–18–08 is $510 per product. which could result in reduced structural
In addition, we estimate that any AD, the regulatory evaluation, any
integrity of the wing.
necessary follow-on actions would take comments received, and other
information. The street address for the (f) Compliance
about 15 work-hours and require parts
costing $10,000, for a cost of $11,275 Docket Operations office (telephone Comply with this AD within the
per product. We have no way of 800–647–5527) is in the ADDRESSES compliance times specified, unless already
determining the number of aircraft that section. done.
might need these actions. List of Subjects in 14 CFR Part 39 (g) Retained Inspection and Corrective
The new requirements of this AD add Action with Additional Repair Information
no additional economic burden. Air transportation, Aircraft, Aviation This paragraph restates the requirements of
safety, Incorporation by reference, paragraph (a) of AD 95–18–08, with
Authority for This Rulemaking Safety. additional repair contact information. Prior
Title 49 of the United States Code to the accumulation of 24,000 total flight
specifies the FAA’s authority to issue Adoption of the Amendment cycles since date of manufacture of the
rules on aviation safety. Subtitle I, airplane, or within 750 flight cycles after
Accordingly, under the authority October 16, 1995 (the effective date of AD
section 106, describes the authority of delegated to me by the Administrator,
the FAA Administrator. ‘‘Subtitle VII: 95–18–08), whichever occurs later, perform a
the FAA amends 14 CFR part 39 as detailed visual inspection to detect cracks in
Aviation Programs,’’ describes in more follows: the bottom skin of the wing in the area of the
detail the scope of the Agency’s cut-out for the pylon rear attachment fitting,
authority. PART 39—AIRWORTHINESS in accordance with Airbus Service Bulletin
We are issuing this rulemaking under DIRECTIVES A300–57–6028, Revision 3, dated September
the authority described in ‘‘Subtitle VII, 13, 1994. Repeat the inspection thereafter at
Part A, Subpart III, Section 44701: ■ 1. The authority citation for part 39 intervals not to exceed 9,000 flight cycles. If
General requirements.’’ Under that continues to read as follows: any crack is detected, prior to further flight,
section, Congress charges the FAA with repair the wing bottom skin in accordance
promoting safe flight of civil aircraft in Authority: 49 U.S.C. 106(g), 40113, 44701. with a method approved by the Manager,
air commerce by prescribing regulations Standardization Branch, ANM–113, FAA,
§ 39.13 [Amended] Transport Airplane Directorate, or the
for practices, methods, and procedures
Manager, International Branch, ANM–116,
the Administrator finds necessary for ■ 2. The FAA amends § 39.13 by
Transport Airplane Directorate, FAA; or the
safety in air commerce. This regulation removing Airworthiness Directive (AD) European Aviation Safety Agency (EASA); or
is within the scope of that authority 95–18–08, Amendment 39–9355 (60 FR Airbus’s EASA Design Organization
because it addresses an unsafe condition 47677, September 14, 1995), and adding Approval (DOA). Accomplishing any
that is likely to exist or develop on the following new AD: inspection required by paragraph (h) of this
products identified in this rulemaking 2016–07–20 Airbus: Amendment 39–18465. AD terminates the inspections required by
action. Docket No. FAA–2015–4817; Directorate this paragraph.
Regulatory Findings Identifier 2014–NM–115–AD. (h) New Requirement of This AD: Revised
(a) Effective Date Inspection Thresholds and Intervals
We determined that this AD will not
have federalism implications under This AD becomes effective May 16, 2016. Within the applicable compliance times
required in paragraphs (h)(1) and (h)(2) of
Executive Order 13132. This AD will (b) Affected ADs this AD, do a detailed visual inspection of
not have a substantial direct effect on the wing bottom skin in the area of the cut-
the States, on the relationship between This AD replaces AD 95–18–08,
Amendment 39–9355 (60 FR 47677, out for the pylon rear attachment fitting on
the national government and the States, September 14, 1995) (‘‘AD 95–18–08’’). left-hand and right-hand wings, in
or on the distribution of power and accordance with the Accomplishment
responsibilities among the various (c) Applicability Instructions of Airbus Service Bulletin A300–
levels of government. This AD applies to the airplanes identified 57–6028, Revision 07, dated June 6, 2011.
For the reasons discussed above, I in paragraphs (c)(1) through (c)(4) of this AD, Repeat the inspections thereafter at the
certify that this AD: certificated in any category, all manufacturer applicable intervals required in paragraphs
1. Is not a ‘‘significant regulatory serial numbers. (h)(3) and (h)(4) of this AD. Accomplishing
action’’ under Executive Order 12866; (1) Airbus Model A300 B4–601, B4–603, any inspection required by this paragraph
2. Is not a ‘‘significant rule’’ under the B4–620, and B4–622 airplanes. terminates the inspections required by
DOT Regulatory Policies and Procedures (2) Airbus Model A300 B4–605R and B4– paragraph (g) of this AD.
622R airplanes. (1) For ‘‘normal range operations’’
(44 FR 11034, February 26, 1979);
jstallworth on DSK7TPTVN1PROD with RULES
(3) Airbus Model A300 F4–605R and F4– airplanes having an average flight time of 1.5
3. Will not affect intrastate aviation in flight hours or more: Do the inspection at the
622R airplanes.
Alaska; and applicable time required in paragraphs
(4) Airbus Model A300 C4–605R Variant F
4. Will not have a significant (h)(1)(i) and (h)(1)(ii) of this AD.
airplanes.
economic impact, positive or negative, (i) For Model A300 F4–605R and F4–622R
on a substantial number of small entities (d) Subject airplanes: Do the inspection at the later of the
under the criteria of the Regulatory Air Transport Association (ATA) of times specified in paragraphs (h)(1)(i)(A) and
Flexibility Act. America Code 57, Wings. (h)(1)(i)(B) of this AD.
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![21258 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations
(A) Within 24,000 flight cycles or 51,800 (1) For the initial inspection, the average actions from a manufacturer, the action must
flight hours after first flight of the airplane, flight time is the total accumulated flight be accomplished using a method approved
whichever occurs first. hours, counted from take-off to touch-down, by the Manager, International Branch, ANM–
(B) Within 2,000 flight cycles or 4,300 divided by the total accumulated flight cycles 116, Transport Airplane Directorate, FAA; or
flight hours after the effective date of this AD, at the effective date of this AD. the EASA; or Airbus’s EASA DOA. If
whichever occurs first. (2) For the first repeated inspection approved by the DOA, the approval must
(ii) For Model A300 B4–600, B4–600R, and interval, the average flight time is the total include the DOA-authorized signature.
Model A300 C4–605R Variant F airplanes: Do accumulated flight hours divided by the total
the inspection at the later of the times accumulated flight cycles at the time of the (m) Related Information
specified in paragraphs (h)(1)(ii)(A) and inspection threshold. (1) Refer to Mandatory Continuing
(h)(1)(ii)(B) of this AD. (3) For all inspection intervals onwards, Airworthiness Information (MCAI) European
(A) Within 19,100 flight cycles or 41,200 the average flight time is the flight hours Aviation Safety Agency Airworthiness
flight hours after first flight of the airplane, divided by the flight cycles accumulated
Directive 2014–0119, dated May 13, 2014, for
whichever occurs first. between the last two inspections.
related information. This MCAI may be
(B) Within 1,500 flight cycles or 3,200
flight hours after the effective date of this AD, (j) New Requirement of This AD: Corrective found in the AD docket on the Internet at
whichever occurs first. Action for Any Cracking Found http://www.regulations.gov by searching for
(2) For ‘‘short range operations’’ airplanes If any crack is found during any inspection and locating Docket No. FAA–2015–4817.
having an average flight time of less than 1.5 required by paragraph (h) of this AD: Before (2) Service information identified in this
flight hours: Do the inspection at the further flight, repair using a method AD that is not incorporated by reference is
applicable time required in paragraphs approved by the Manager, International available at the addresses specified in
(h)(2)(i) and (h)(2)(ii) of this AD. Branch, ANM–116, Transport Airplane paragraphs (n)(5) and (n)(6) of this AD.
(i) For Model A300 F4–605R and F4–622R Directorate, FAA; or EASA; or Airbus’s EASA
(n) Material Incorporated by Reference
airplanes: Do the inspection at the later of the DOA. Accomplishing a repair does not
times specified in paragraphs (h)(2)(i)(A) and constitute terminating action for the (1) The Director of the Federal Register
(h)(2)(i)(B) of this AD. repetitive inspections required by paragraph approved the incorporation by reference
(A) Within 25,900 flight cycles or 38,800 (h) of this AD. (IBR) of the service information listed in this
flight hours after first flight of the airplane, paragraph under 5 U.S.C. 552(a) and 1 CFR
whichever occurs first. (k) Credit for Previous Actions part 51.
(B) Within 2,100 flight cycles or 3,200 This paragraph provides credit for (2) You must use this service information
flight hours after the effective date of this AD, inspections required by paragraph (h) of this as applicable to do the actions required by
whichever occurs first. AD, if those actions were performed before this AD, unless this AD specifies otherwise.
(ii) For Model A300 B4–600, B4–600R, and the effective date of this AD using any of the (3) The following service information was
Model A300 C4–605R Variant F airplanes: Do service information identified in paragraphs approved for IBR on May 16, 2016.
the inspection at the later of the times (k)(1), (k)(2), and (k)(3) of this AD, which are (i) Airbus Service Bulletin A300–57–6028,
specified in paragraphs (h)(2)(ii)(A) and not incorporated by reference in this AD. Revision 07, dated June 6, 2011.
(h)(2)(ii)(B) of this AD. (1) Airbus Service Bulletin A300–57–6028, (ii) Reserved.
(A) Within 20,600 flight cycles or 30,900 Revision 04, dated October 25, 1999. (4) The following service information was
flight hours after first flight of the airplane, (2) Airbus Service Bulletin A300–57–6028, approved for IBR on October 16, 1995 (60 FR
whichever occurs first. Revision 05, dated January 11, 2002. 47677, September 14, 1995).
(B) Within 1,600 flight cycles or 2,400 (3) Airbus Service Bulletin A300–57–6028,
(i) Airbus Service Bulletin A300–57–6028,
flight hours after the effective date of this AD, Revision 06, dated May 17, 2006.
Revision 3, dated September 13, 1994. Pages
whichever occurs first.
(l) Other FAA AD Provisions 1 through 6 of this service bulletin indicate
(3) For ‘‘normal range operations’’
airplanes having an average flight time of 1.5 The following provisions also apply to this Revision 3 and are dated September 13, 1994;
flight hours or more: Repeat the inspection at AD: pages 7 through 9 indicate Revision 2 and are
the applicable time required in paragraphs (1) Alternative Methods of Compliance dated February 22, 1994.
(h)(3)(i) and (h)(3)(ii) of this AD. (AMOCs): The Manager, International (ii) Reserved.
(i) For Model A300 F4–605R and F4–622R Branch, ANM–116, Transport Airplane (5) For service information identified in
airplanes: Repeat the inspection thereafter at Directorate, FAA, has the authority to this AD, contact Airbus SAS, Airworthiness
intervals not to exceed 9,000 flight cycles or approve AMOCs for this AD, if requested Office—EAW, 1 Rond Point Maurice
19,400 flight hours, whichever occurs first. using the procedures found in 14 CFR 39.19. Bellonte, 31707 Blagnac Cedex, France;
(ii) For Model A300 B4–600, B4–600R, and In accordance with 14 CFR 39.19, send your telephone +33 5 61 93 36 96; fax +33 5 61
Model A300 C4–605R Variant F airplanes: request to your principal inspector or local 93 44 51; email account.airworth-eas@
Repeat the inspection thereafter at intervals Flight Standards District Office, as airbus.com; Internet http://www.airbus.com.
not to exceed 7,100 flight cycles or 15,300 appropriate. If sending information directly (6) You may view this service information
flight hours, whichever occurs first. to the International Branch, send it to ATTN: at the FAA, Transport Airplane Directorate,
(4) For ‘‘short range operations’’ airplanes Dan Rodina, Aerospace Engineer, 1601 Lind Avenue SW., Renton, WA. For
having an average flight time of less than 1.5 International Branch, ANM–116, Transport information on the availability of this
flight hours: Repeat the inspection at the Airplane Directorate, FAA, 1601 Lind material at the FAA, call 425–227–1221.
applicable time required in paragraphs Avenue SW., Renton, WA 98057–3356; (7) You may view this service information
(h)(4)(i) and (h)(4)(ii) of this AD. telephone 425–227–2125; fax 425–227–1149. that is incorporated by reference at the
(i) For Model A300 F4–605R and F4–622R Information may be emailed to: 9-ANM-116- National Archives and Records
airplanes: Repeat the inspection thereafter at AMOC-REQUESTS@faa.gov. Administration (NARA). For information on
intervals not to exceed 9,700 flight cycles or (i) Before using any approved AMOC, the availability of this material at NARA, call
14,500 flight hours, whichever occurs first. notify your appropriate principal inspector, 202–741–6030, or go to: http://
(ii) For Model A300 B4–600, B4–600R, and or lacking a principal inspector, the manager www.archives.gov/federal-register/cfr/ibr-
Model A300 C4–605R Variant F airplanes: of the local flight standards district office/
locations.html.
Repeat the inspection thereafter at intervals certificate holding district office. The AMOC
jstallworth on DSK7TPTVN1PROD with RULES
not to exceed 7,600 flight cycles or 11,500 approval letter must specifically reference Issued in Renton, Washington, on March
flight hours, whichever occurs first. this AD. 24, 2016.
(ii) AMOCs approved previously for AD Michael Kaszycki,
(i) Definition of Average Flight Time for 95–18–08, are approved as AMOCs for the
Paragraph (h) of This AD Acting Manager, Transport Airplane
corresponding provisions of paragraph (g) of
Directorate, Aircraft Certification Service.
For the purpose of paragraph (h) of this this AD.
AD, the Average Flight Time must be (2) Contacting the Manufacturer: For any [FR Doc. 2016–07570 Filed 4–8–16; 8:45 am]
established as follows: requirement in this AD to obtain corrective BILLING CODE 4910–13–P
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Document Created: 2016-04-09 00:11:24
Document Modified: 2016-04-09 00:11:24
| 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 May 16, 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 21255 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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