82 FR 52832 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 219 (November 15, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 219 (November 15, 2017)
| Page Range | 52832-52835 | |
| FR Document | 2017-24501 |
[Federal Register Volume 82, Number 219 (Wednesday, November 15, 2017)] [Rules and Regulations] [Pages 52832-52835] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-24501] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0710; Product Identifier 2017-NM-019-AD; Amendment 39-19098; AD 2017-23-04] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-600R series airplanes; Model A300 B4-603, B4-620, and B4-622 airplanes; Model A300 C4-605R Variant F airplanes; and Model A300 F4-605R airplanes. This AD was prompted by a determination that the top stringer joints at rib 18 are an area of uniform stress distribution, which indicates that cracks may develop in adjacent stringers at the same time. This AD requires an inspection of the upper wing skin and top stringer joints, and modification of the stringer joint couplings if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective December 20, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 20, 2017. 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 Standards Branch, 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-2017- 0710. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017- 0710; 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 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 Section, Transport Standards Branch, 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 by adding an AD that would apply to certain Airbus Model A300 B4-600R series airplanes; Model A300 B4-603, B4-620, and B4-622 airplanes; [[Page 52833]] Model A300 C4-605R Variant F airplanes; and Model A300 F4-605R airplanes. The NPRM published in the Federal Register on July 27, 2017 (82 FR 34885) (``the NPRM''). The NPRM was prompted by a determination that the top stringer joints at rib 18 are an area of uniform stress distribution, which indicates that cracks may develop in adjacent stringers at the same time. The NPRM proposed to require an inspection of the upper wing skin and top stringer joints, and modification of the stringer joint couplings if necessary. We are issuing this AD to detect and correct damage (including cracking) at the stringer joints, which could reduce the 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 AD 2017-0023, dated February 10, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A300 B4-600R series airplanes; Model A300 B4-603, B4-620, and B4-622 airplanes; Model A300 C4-605R Variant F airplanes; and Model A300 F4-605R airplanes. The MCAI states: In response to the FAA Part 26 rule change concerning Widespread Fatigue Damage (WFD), all wing structural items of the A300-600 design deemed potentially susceptible to WFD were assessed. The top stringer joints at Rib 18 were highlighted as an area of uniform stress distribution, indicating that cracks may develop in adjacent stringers at the same time which is known as Multi Element Damage (MED). Each affected stringer joint consists of three main load transferring parts: An overlapping flange, two straps attached through the stringer web and a strap on the top flange. All the components of the joint are attached with fasteners. The fastener holes were the subject of a MED WFD analysis, which showed that cracking could occur from a number of the holes in the joint on stringers 11, 12, 13, 14, 15, 16, 17, and 18. This condition, if not detected and corrected, could reduce the structural integrity of the wing. Prompted by the conclusion of the WFD analysis, Airbus issued Service Bulletin (SB) A300-57-6118 to provide modification instructions. The modification will both re-life via oversizing and inspect via non-destructive test a defined number of stringer joint fastener holes at Rib 18. This modification will delay the onset of cracking at the stringer joint, providing it is completed at the specified time and will delay the requirement for subsequent inspection. For the reasons described above, this [EASA] AD requires a detailed visual inspection (DVI) [for damage, including cracking] of the upper wing skin and the top stringer joints at Rib 18, [and corrective action if necessary] and modification of the stringer joint couplings at Rib 18, on both wings [as applicable]. The modification includes a related investigative action, i.e., a special detailed (roto-probe) inspection for damage, including cracking, of the fastener holes in the upper wing skin, and corrective action if necessary. Corrective actions include repairing any damage. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017- 0710. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Request To Update the Costs of Compliance FedEx supported the intent of the NPRM, but requested that we update the parts cost in the Costs of Compliance section of the proposed AD to reflect the cost of two parts kits. FedEx noted that the proposed AD listed the parts cost for only one kit. FedEx pointed out that operators may need to modify both wings and could therefore need two parts kits per airplane. We agree with the commenter's request. We have revised the Costs of Compliance section of this final rule to reflect two parts kits, each costing $4,770. Request To Fix a Typographical Error Airbus requested that we correct a reference to ``Airbus Model A300 C4-605 Variant F'' airplanes in paragraph (g)(2) of the proposed AD. The correct model name is ``A300 C4-605R Variant F'' airplanes. We agree with the commenter's request. We have corrected the typographical error in this AD. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A300-57-6118, Revision 01, dated January 31, 2017. This service information describes procedures for an inspection of the upper wing skin and top stringer joints at rib 18, and modification of the stringer joint couplings. 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 65 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs -------------------------------------------------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product Cost on U.S. operators -------------------------------------------------------------------------------------------------------------------------------------------------------- Inspection and modification....... 37 work-hours x $85 per Up to $9,540................ Up to $12,685............... Up to $824,525. hour = $3,145. -------------------------------------------------------------------------------------------------------------------------------------------------------- We have received no definitive data that will allow us to provide cost estimates for certain on-condition 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. [[Page 52834]] 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. 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 adding the following new airworthiness directive (AD): 2017-23-04 Airbus: Amendment 39-19098; Docket No. FAA-2017-0710; Product Identifier 2017-NM-019-AD. (a) Effective Date This AD is effective December 20, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A300 B4-605R, B4-622R, B4-603, C4-605R Variant F, B4-620, B4-622, and F4-605R airplanes, certificated in any category, all serial numbers except Model A300 F4-605R airplanes that have embodied Airbus modification 12699 in production. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a determination that the top stringer joints at rib 18 are an area of uniform stress distribution, which indicates that cracks may develop in adjacent stringers at the same time. We are issuing this AD to detect and correct damage (including cracking) at the stringer joints, which could reduce the structural integrity of the wing. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definitions For the purposes of this AD, the definitions in paragraphs (g)(1) through (g)(5) of this AD apply. (1) Group 1 airplanes are defined as Airbus Model A300 B4-603, B4-605R, B4-620, B4-622, and B4-622R airplanes. (2) Group 2 airplanes are defined as Airbus Model A300 C4-605R Variant F and F4-605R (if in pre-modification 12699 configuration) airplanes. (3) Short range (SR) is defined as airplanes with an average flight time of less than 1.5 flight hours per flight cycle. (4) Long range (LR) is defined as airplanes with an average flight time equal to or higher than 1.5 flight hours per flight cycle. (5) For determining the ``short range'' and ``long range'' airplanes, 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. (h) Inspection and Modification Not before exceeding the applicable lower thresholds as specified in table 1 to paragraph (h) of this AD, and within the compliance times specified in paragraphs (h)(1), (h)(2), (h)(3), and (h)(4) of this AD, as applicable: Accomplish a detailed visual inspection for damage (including cracking) of the upper wing skin and top stringer joints at rib 18 on both wings, do all applicable corrective actions, and do the applicable modification, including related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6118, Revision 01, dated January 31, 2017, except as required by paragraph (i) of this AD. Do all applicable modifications, related investigative actions, and corrective actions before further flight. (1) For Group 1, LR airplanes: Inspect at the time specified in paragraph (h)(1)(i) or (h)(1)(ii) of this AD, whichever occurs later. (i) Before exceeding 32,500 flight cycles or 70,300 flight hours, whichever occurs first since first flight of the airplane. (ii) Within 700 flight cycles, 1,500 flight hours, or 12 months, whichever occurs first after the effective date of this AD. (2) For Group 1, SR airplanes: Inspect at the time specified in paragraphs (h)(2)(i) or (h)(2)(ii) of this AD, whichever occurs later. (i) Before exceeding 35,100 flight cycles or 52,600 flight hours, whichever occurs first since the first flight of the airplane. (ii) Within 700 flight cycles or 1,000 flight hours, or 12 months, whichever occurs first after the effective date of this AD. (3) For Group 2, LR airplanes: Inspect before exceeding 35,000 flight cycles or 75,700 flight hours, whichever occurs first since the first flight of the airplane. (4) For Group 2, SR airplanes: Inspect before exceeding 37,800 flight cycles or 56,700 flight hours, whichever occurs first since the first flight of the airplane. Table 1 to Paragraph (h) of This AD--Compliance Time Lower Thresholds ------------------------------------------------------------------------ Compliance time flight cycles (FC) or flight hours (FH), whichever Applicable airplanes occurs first since first flight of the airplane ------------------------------------------------------------------------ Group 1, LR....................... Not before exceeding 30,900 FC or 66,700 FH. Group 1, SR....................... Not before exceeding 28,700 FC or 43,000 FH. Group 2, LR....................... Not before exceeding 28,600 FC or 61,700 FH. Group 2, SR....................... Not before exceeding 34,400 FC or 51,600 FH. ------------------------------------------------------------------------ (i) Service Information Exception Where Airbus Service Bulletin A300-57-6118, Revision 01, dated January 31, 2017, specifies to contact Airbus for appropriate action, and specifies that action as ``RC'' (Required for Compliance): Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (k)(2) of this AD. (j) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A300-57-6118, dated June 30, 2015. (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International [[Page 52835]] Section, Transport Standards Branch, 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 Section, send it to the attention of the person identified in paragraph (l)(2) of this AD. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA- authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (i) of this AD, if any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017-0023, dated February 10, 2017, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-0710. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (m)(4) of this AD. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A300-57-6118, Revision 01, dated January 31, 2017. (ii) Reserved. (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 Standards Branch, 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 November 3, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017-24501 Filed 11-14-17; 8:45 am] BILLING CODE 4910-13-P
![52832 Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations
(d) Subject Burlington, MA 01803; phone: 781–238– indicates that cracks may develop in
Joint Aircraft System Component (JASC) 7754; fax: 781–238–7199; email: john.frost@ adjacent stringers at the same time. This
Code 7531, Compressor bleed governor. faa.gov. AD requires an inspection of the upper
(e) Unsafe Condition (k) Material Incorporated by Reference wing skin and top stringer joints, and
(1) The Director of the Federal Register modification of the stringer joint
This AD was prompted by an engine fire
that occurred as a result of malfunctions approved the incorporation by reference couplings if necessary. We are issuing
related to the operability bleed valve (OBV). (IBR) of the service information listed in this this AD to address the unsafe condition
We are issuing this AD to prevent failure of paragraph under 5 U.S.C. 552(a) and 1 CFR on these products.
the OBV. The unsafe condition, if not part 51. DATES: This AD is effective December
corrected, could result in failure of the OBV, (2) You must use this service information
as applicable to do the actions required by
20, 2017.
engine fire, and damage to the airplane. The Director of the Federal Register
this AD, unless the AD specifies otherwise.
(f) Compliance (i) General Electric Company (GE) Service approved the incorporation by reference
Comply with this AD within the Bulletin CF34–8C–AL S/B 75–0019 Revision of a certain publication listed in this AD
compliance times specified, unless already 01, dated October 24, 2017. as of December 20, 2017.
done. (ii) Reserved. ADDRESSES: For service information
(3) For GE service information identified in identified in this final rule, contact
(g) Required Actions this AD, contact General Electric Company, Airbus SAS, Airworthiness Office—
(1) Inspect the bleed air manifold link rod GE-Aviation, Room 285, 1 Neumann Way,
assemblies and the OBV supply, return, and EAW, 1 Rond Point Maurice Bellonte,
Cincinnati, OH 45215, phone: 513–552–3272;
drain fuel fittings within 500 flight hours fax: 513–552–3329; email: geae.aoc@ge.com. 31707 Blagnac Cedex, France; telephone
after the effective date of this AD. (4) You may view this service information +33 5 61 93 36 96; fax +33 5 61 93 44
(2) Use the Accomplishment Instructions, at FAA, FAA, Engine & Propeller Standards 51; email account.airworth-eas@
paragraph 3.B., in GE Service Bulletin (SB) Branch, 1200 District Avenue, Burlington, airbus.com; Internet http://
CF34–8C–AL S/B 75–0019 Revision 01, dated MA. For information on the availability of www.airbus.com. You may view this
October 24, 2017, to do the inspection. this material at the FAA, call 781–238–7125. referenced service information at the
Replace parts that fail this inspection (5) You may view this service information FAA, Transport Standards Branch, 1601
according to the following criteria: that is incorporated by reference at the
(i) Replace any OBV that fails the
Lind Avenue SW., Renton, WA. For
National Archives and Records
inspection with a part eligible for installation information on the availability of this
Administration (NARA). For information on
before further flight. the availability of this material at NARA, call material at the FAA, call 425–227–1221.
(ii) Replace any additional hardware that 202–741–6030, or go to: http:// It is also available on the Internet at
fails inspection within 50 flight cycles. The www.archives.gov/federal-register/cfr/ibr- http://www.regulations.gov by searching
engine can be returned to service each day locations.html. for and locating Docket No. FAA–2017–
for up to the 50 flight cycles if the OBV rosan 0710.
rings and fittings are examined each day for Issued in Burlington, Massachusetts, on
fuel leaks and looseness based on the criteria November 9, 2017. Examining the AD Docket
in Table 1 of GE SB CF34–8C–AL S/B 75– Robert J. Ganley,
You may examine the AD docket on
0019 Revision 01, dated October 24, 2017. Manager, Engine and Propeller Standards
(3) The reporting instructions in the Internet at http://
Branch, Aircraft Certification Service.
paragraphs 3.B.(3), 3.B.(5)(e), 3.B.(6)(e), and www.regulations.gov by searching for
[FR Doc. 2017–24700 Filed 11–14–17; 8:45 am]
3.B.(8) of GE SB CF34–8C–AL S/B 75–0019 and locating Docket No. FAA–2017–
Revision 01, dated October 24, 2017, are not BILLING CODE 4910–13–P 0710; or in person at the Docket
required by this AD. Management Facility between 9 a.m.
(h) Credit for Previous Actions and 5 p.m., Monday through Friday,
DEPARTMENT OF TRANSPORTATION except Federal holidays. The AD docket
You may take credit for the actions that are
required by paragraph (g) of this AD if you Federal Aviation Administration contains this AD, the regulatory
performed these actions before the effective evaluation, any comments received, and
date of this AD using GE CF34–8C SB 75– 14 CFR Part 39 other information. The street address for
0019 R00, dated August 4, 2017. the Docket Office (telephone 800–647–
[Docket No. FAA–2017–0710; Product 5527) is Docket Management Facility,
(i) Alternative Methods of Compliance Identifier 2017–NM–019–AD; Amendment
(AMOCs) U.S. Department of Transportation,
39–19098; AD 2017–23–04] Docket Operations, M–30, West
(1) The Manager, ECO Branch, FAA, has
the authority to approve AMOCs for this AD, RIN 2120–AA64 Building Ground Floor, Room W12–140,
if requested using the procedures found in 14 1200 New Jersey Avenue SE.,
CFR 39.19. In accordance with 14 CFR 39.19, Airworthiness Directives; Airbus Washington, DC 20590.
send your request to your principal inspector Airplanes FOR FURTHER INFORMATION CONTACT: Dan
or local Flight Standards District Office, as AGENCY: Federal Aviation Rodina, Aerospace Engineer,
appropriate. If sending information directly International Section, Transport
to the manager of the certification office, Administration (FAA), Department of
Transportation (DOT). Standards Branch, FAA, 1601 Lind
send it to the attention of the person
identified in paragraph (j) of this AD. You ACTION: Final rule. Avenue SW., Renton, WA 98057–3356;
may email your request to: ANE-AD-AMOC@ telephone 425–227–2125; fax 425–227–
faa.gov. SUMMARY: We are adopting a new 1149.
(2) Before using any approved AMOC, airworthiness directive (AD) for certain SUPPLEMENTARY INFORMATION:
notify your appropriate principal inspector, Airbus Model A300 B4–600R series
sradovich on DSK3GMQ082PROD with RULES
or lacking a principal inspector, the manager airplanes; Model A300 B4–603, B4–620, Discussion
of the local flight standards district office/ and B4–622 airplanes; Model A300 C4– We issued a notice of proposed
certificate holding district office. 605R Variant F airplanes; and Model rulemaking (NPRM) to amend 14 CFR
(j) Related Information A300 F4–605R airplanes. This AD was part 39 by adding an AD that would
For more information about this AD, prompted by a determination that the apply to certain Airbus Model A300 B4–
contact John Frost, Aerospace Engineer, ECO top stringer joints at rib 18 are an area 600R series airplanes; Model A300 B4–
Branch, FAA, 1200 District Avenue, of uniform stress distribution, which 603, B4–620, and B4–622 airplanes;
VerDate Sep<11>2014 15:48 Nov 14, 2017 Jkt 244001 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 E:\FR\FM\15NOR1.SGM 15NOR1](https://thefederalregister.org/doc/82_FR_53051/page/1.svg)
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Model A300 C4–605R Variant F Prompted by the conclusion of the WFD reflect two parts kits, each costing
airplanes; and Model A300 F4–605R analysis, Airbus issued Service Bulletin (SB) $4,770.
airplanes. The NPRM published in the A300–57–6118 to provide modification
instructions. The modification will both re- Request To Fix a Typographical Error
Federal Register on July 27, 2017 (82 FR
life via oversizing and inspect via non-
34885) (‘‘the NPRM’’). The NPRM was Airbus requested that we correct a
destructive test a defined number of stringer
prompted by a determination that the joint fastener holes at Rib 18. This reference to ‘‘Airbus Model A300 C4–
top stringer joints at rib 18 are an area modification will delay the onset of cracking 605 Variant F’’ airplanes in paragraph
of uniform stress distribution, which at the stringer joint, providing it is completed (g)(2) of the proposed AD. The correct
indicates that cracks may develop in at the specified time and will delay the model name is ‘‘A300 C4–605R Variant
adjacent stringers at the same time. The requirement for subsequent inspection. F’’ airplanes.
NPRM proposed to require an For the reasons described above, this We agree with the commenter’s
inspection of the upper wing skin and [EASA] AD requires a detailed visual request. We have corrected the
inspection (DVI) [for damage, including typographical error in this AD.
top stringer joints, and modification of
cracking] of the upper wing skin and the top
the stringer joint couplings if necessary. stringer joints at Rib 18, [and corrective Conclusion
We are issuing this AD to detect and action if necessary] and modification of the
correct damage (including cracking) at stringer joint couplings at Rib 18, on both We reviewed the relevant data,
the stringer joints, which could reduce wings [as applicable]. considered the comments received, and
the structural integrity of the wing. determined that air safety and the
The modification includes a related public interest require adopting this AD
The European Aviation Safety Agency investigative action, i.e., a special with the changes described previously
(EASA), which is the Technical Agent detailed (roto-probe) inspection for and minor editorial changes. We have
for the Member States of the European damage, including cracking, of the determined that these minor changes:
Union, has issued EASA AD 2017–0023, fastener holes in the upper wing skin, • Are consistent with the intent that
dated February 10, 2017 (referred to and corrective action if necessary. was proposed in the NPRM for
after this as the Mandatory Continuing Corrective actions include repairing any correcting the unsafe condition; and
Airworthiness Information, or ‘‘the damage. • Do not add any additional burden
MCAI’’), to correct an unsafe condition You may examine the MCAI in the upon the public than was already
for certain Airbus Model A300 B4–600R AD docket on the Internet at http:// proposed in the NPRM.
series airplanes; Model A300 B4–603, www.regulations.gov by searching for We also determined that these
B4–620, and B4–622 airplanes; Model and locating Docket No. FAA–2017– changes will not increase the economic
A300 C4–605R Variant F airplanes; and 0710. burden on any operator or increase the
Model A300 F4–605R airplanes. The
Comments scope of this AD.
MCAI states:
In response to the FAA Part 26 rule change We gave the public the opportunity to Related Service Information Under 1
concerning Widespread Fatigue Damage participate in developing this AD. The CFR Part 51
(WFD), all wing structural items of the A300– following presents the comments Airbus has issued Service Bulletin
600 design deemed potentially susceptible to received on the NPRM and the FAA’s A300–57–6118, Revision 01, dated
WFD were assessed. The top stringer joints response to each comment. January 31, 2017. This service
at Rib 18 were highlighted as an area of
uniform stress distribution, indicating that Request To Update the Costs of information describes procedures for an
cracks may develop in adjacent stringers at Compliance inspection of the upper wing skin and
the same time which is known as Multi top stringer joints at rib 18, and
Element Damage (MED). Each affected FedEx supported the intent of the modification of the stringer joint
stringer joint consists of three main load NPRM, but requested that we update the couplings. This service information is
transferring parts: An overlapping flange, two parts cost in the Costs of Compliance reasonably available because the
straps attached through the stringer web and section of the proposed AD to reflect the interested parties have access to it
a strap on the top flange. All the components cost of two parts kits. FedEx noted that through their normal course of business
of the joint are attached with fasteners. The the proposed AD listed the parts cost for or by the means identified in the
fastener holes were the subject of a MED only one kit. FedEx pointed out that ADDRESSES section.
WFD analysis, which showed that cracking operators may need to modify both
could occur from a number of the holes in Costs of Compliance
wings and could therefore need two
the joint on stringers 11, 12, 13, 14, 15, 16,
17, and 18. parts kits per airplane. We estimate that this AD affects 65
This condition, if not detected and We agree with the commenter’s airplanes of U.S. registry.
corrected, could reduce the structural request. We have revised the Costs of We estimate the following costs to
integrity of the wing. Compliance section of this final rule to comply with this AD:
ESTIMATED COSTS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
Inspection and modification ................. 37 work-hours × $85 per hour = Up to $9,540 ......... Up to $12,685 ....... Up to $824,525.
$3,145.
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We have received no definitive data Authority for This Rulemaking section 106, describes the authority of
that will allow us to provide cost the FAA Administrator. ‘‘Subtitle VII:
estimates for certain on-condition Title 49 of the United States Code Aviation Programs,’’ describes in more
actions specified in this AD. specifies the FAA’s authority to issue detail the scope of the Agency’s
rules on aviation safety. Subtitle I, authority.
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![52834 Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations
We are issuing this rulemaking under Authority: 49 U.S.C. 106(g), 40113, 44701. the upper wing skin and top stringer joints
the authority described in ‘‘Subtitle VII, at rib 18 on both wings, do all applicable
§ 39.13 [Amended] corrective actions, and do the applicable
Part A, Subpart III, Section 44701:
■ 2. The FAA amends § 39.13 by adding modification, including related investigative
General requirements.’’ Under that and corrective actions, in accordance with
section, Congress charges the FAA with the following new airworthiness
the Accomplishment Instructions of Airbus
promoting safe flight of civil aircraft in directive (AD): Service Bulletin A300–57–6118, Revision 01,
air commerce by prescribing regulations 2017–23–04 Airbus: Amendment 39–19098; dated January 31, 2017, except as required by
for practices, methods, and procedures Docket No. FAA–2017–0710; Product paragraph (i) of this AD. Do all applicable
the Administrator finds necessary for Identifier 2017–NM–019–AD. modifications, related investigative actions,
safety in air commerce. This regulation and corrective actions before further flight.
(a) Effective Date (1) For Group 1, LR airplanes: Inspect at
is within the scope of that authority
This AD is effective December 20, 2017. the time specified in paragraph (h)(1)(i) or
because it addresses an unsafe condition (h)(1)(ii) of this AD, whichever occurs later.
that is likely to exist or develop on (b) Affected ADs (i) Before exceeding 32,500 flight cycles or
products identified in this rulemaking None. 70,300 flight hours, whichever occurs first
action. since first flight of the airplane.
This AD is issued in accordance with (c) Applicability
(ii) Within 700 flight cycles, 1,500 flight
authority delegated by the Executive This AD applies to Airbus Model A300 B4– hours, or 12 months, whichever occurs first
Director, Aircraft Certification Service, 605R, B4–622R, B4–603, C4–605R Variant F, after the effective date of this AD.
as authorized by FAA Order 8000.51C. B4–620, B4–622, and F4–605R airplanes, (2) For Group 1, SR airplanes: Inspect at
certificated in any category, all serial the time specified in paragraphs (h)(2)(i) or
In accordance with that order, issuance numbers except Model A300 F4–605R (h)(2)(ii) of this AD, whichever occurs later.
of ADs is normally a function of the airplanes that have embodied Airbus (i) Before exceeding 35,100 flight cycles or
Compliance and Airworthiness modification 12699 in production. 52,600 flight hours, whichever occurs first
Division, but during this transition since the first flight of the airplane.
period, the Executive Director has (d) Subject
(ii) Within 700 flight cycles or 1,000 flight
delegated the authority to issue ADs Air Transport Association (ATA) of hours, or 12 months, whichever occurs first
applicable to transport category America Code 57, Wings. after the effective date of this AD.
airplanes to the Director of the System (3) For Group 2, LR airplanes: Inspect
(e) Reason
before exceeding 35,000 flight cycles or
Oversight Division. This AD was prompted by a determination 75,700 flight hours, whichever occurs first
Regulatory Findings that the top stringer joints at rib 18 are an since the first flight of the airplane.
area of uniform stress distribution, which (4) For Group 2, SR airplanes: Inspect
We determined that this AD will not indicates that cracks may develop in adjacent before exceeding 37,800 flight cycles or
have federalism implications under stringers at the same time. We are issuing this 56,700 flight hours, whichever occurs first
Executive Order 13132. This AD will AD to detect and correct damage (including since the first flight of the airplane.
not have a substantial direct effect on cracking) at the stringer joints, which could
the States, on the relationship between reduce the structural integrity of the wing. TABLE 1 TO PARAGRAPH (h) OF THIS
the national government and the States, (f) Compliance AD—COMPLIANCE TIME LOWER
or on the distribution of power and Comply with this AD within the THRESHOLDS
responsibilities among the various compliance times specified, unless already
levels of government. done. Compliance time flight cycles
For the reasons discussed above, I Applicable (FC) or flight hours (FH),
(g) Definitions airplanes whichever occurs first since
certify that this AD: first flight of the airplane
1. Is not a ‘‘significant regulatory For the purposes of this AD, the definitions
action’’ under Executive Order 12866; in paragraphs (g)(1) through (g)(5) of this AD Group 1, LR Not before exceeding 30,900 FC or
apply. 66,700 FH.
2. Is not a ‘‘significant rule’’ under the Group 1, SR Not before exceeding 28,700 FC or
DOT Regulatory Policies and Procedures (1) Group 1 airplanes are defined as Airbus 43,000 FH.
(44 FR 11034, February 26, 1979); Model A300 B4–603, B4–605R, B4–620, B4– Group 2, LR Not before exceeding 28,600 FC or
3. Will not affect intrastate aviation in 622, and B4–622R airplanes. 61,700 FH.
(2) Group 2 airplanes are defined as Airbus Group 2, SR Not before exceeding 34,400 FC or
Alaska; and Model A300 C4–605R Variant F and F4–605R 51,600 FH.
4. Will not have a significant (if in pre-modification 12699 configuration)
economic impact, positive or negative, airplanes. (i) Service Information Exception
on a substantial number of small entities (3) Short range (SR) is defined as airplanes Where Airbus Service Bulletin A300–57–
under the criteria of the Regulatory with an average flight time of less than 1.5 6118, Revision 01, dated January 31, 2017,
Flexibility Act. flight hours per flight cycle. specifies to contact Airbus for appropriate
(4) Long range (LR) is defined as airplanes action, and specifies that action as ‘‘RC’’
List of Subjects in 14 CFR Part 39 with an average flight time equal to or higher (Required for Compliance): Before further
Air transportation, Aircraft, Aviation than 1.5 flight hours per flight cycle. flight, accomplish corrective actions in
safety, Incorporation by reference, (5) For determining the ‘‘short range’’ and accordance with the procedures specified in
Safety. ‘‘long range’’ airplanes, the average flight paragraph (k)(2) of this AD.
time is the total accumulated flight hours,
Adoption of the Amendment counted from take-off to touch-down, divided (j) Credit for Previous Actions
by the total accumulated flight cycles at the This paragraph provides credit for actions
Accordingly, under the authority
effective date of this AD. required by paragraph (h) of this AD, if those
delegated to me by the Administrator, actions were performed before the effective
the FAA amends 14 CFR part 39 as (h) Inspection and Modification
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date of this AD using Airbus Service Bulletin
follows: Not before exceeding the applicable lower A300–57–6118, dated June 30, 2015.
thresholds as specified in table 1 to
PART 39—AIRWORTHINESS paragraph (h) of this AD, and within the (k) Other FAA AD Provisions
DIRECTIVES compliance times specified in paragraphs The following provisions also apply to this
(h)(1), (h)(2), (h)(3), and (h)(4) of this AD, as AD:
■ 1. The authority citation for part 39 applicable: Accomplish a detailed visual (1) Alternative Methods of Compliance
continues to read as follows: inspection for damage (including cracking) of (AMOCs): The Manager, International
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![Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations 52835
Section, Transport Standards Branch, FAA, (ii) Reserved. Boeing Commercial Airplanes,
has the authority to approve AMOCs for this (3) For service information identified in Attention: Contractual & Data Services
AD, if requested using the procedures found this AD, contact Airbus SAS, Airworthiness (C&DS), 2600 Westminster Blvd., MC
in 14 CFR 39.19. In accordance with 14 CFR Office—EAW, 1 Rond Point Maurice 110–SK57, Seal Beach, CA 90740–5600;
39.19, send your request to your principal Bellonte, 31707 Blagnac Cedex, France;
inspector or local Flight Standards District telephone +33 5 61 93 36 96; fax +33 5 61
telephone 562–797–1717; Internet
Office, as appropriate. If sending information 93 44 51; email account.airworth-eas@ https://www.myboeingfleet.com. You
directly to the International Section, send it airbus.com; Internet http://www.airbus.com. may view this referenced service
to the attention of the person identified in (4) You may view this service information information at the FAA, Transport
paragraph (l)(2) of this AD. Information may at the FAA, Transport Standards Branch, Standards Branch, 1601 Lind Avenue
be emailed to: 9-ANM-116-AMOC- 1601 Lind Avenue SW., Renton, WA. For SW., Renton, WA. For information on
REQUESTS@faa.gov. Before using any information on the availability of this the availability of this material at the
approved AMOC, notify your appropriate material at the FAA, call 425–227–1221. FAA, call 425–227–1221. It is also
principal inspector, or lacking a principal (5) You may view this service information available on the Internet at http://
inspector, the manager of the local flight that is incorporated by reference at the
standards district office/certificate holding National Archives and Records
www.regulations.gov by searching for
district office. Administration (NARA). For information on and locating Docket No. FAA–2017–
(2) Contacting the Manufacturer: For any the availability of this material at NARA, call 0715.
requirement in this AD to obtain corrective 202–741–6030, or go to: http:// Examining the AD Docket
actions from a manufacturer, the action must www.archives.gov/federal-register/cfr/ibr-
be accomplished using a method approved locations.html. You may examine the AD docket on
by the Manager, International Section,
Issued in Renton, Washington, on the Internet at http://
Transport Standards Branch, FAA; or the www.regulations.gov by searching for
November 3, 2017.
European Aviation Safety Agency (EASA); or and locating Docket No. FAA–2017–
Airbus’s EASA Design Organization Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
0715; or in person at the Docket
Approval (DOA). If approved by the DOA,
the approval must include the DOA- Certification Service. Management Facility between 9 a.m.
authorized signature. [FR Doc. 2017–24501 Filed 11–14–17; 8:45 am]
and 5 p.m., Monday through Friday,
(3) Required for Compliance (RC): Except except Federal holidays. The AD docket
BILLING CODE 4910–13–P
as required by paragraph (i) of this AD, if any contains this final rule, the regulatory
service information contains procedures or evaluation, any comments received, and
tests that are identified as RC, those
DEPARTMENT OF TRANSPORTATION other information. The address for the
procedures and tests must be done to comply Docket Office (phone: 800–647–5527) is
with this AD; any procedures or tests that are Docket Management Facility, U.S.
Federal Aviation Administration
not identified as RC are recommended. Those Department of Transportation, Docket
procedures and tests that are not identified
as RC may be deviated from using accepted 14 CFR Part 39 Operations, M–30, West Building
methods in accordance with the operator’s Ground Floor, Room W12–140, 1200
[Docket No. FAA–2017–0715; Product New Jersey Avenue SE., Washington,
maintenance or inspection program without Identifier 2017–NM–073–AD; Amendment
obtaining approval of an AMOC, provided 39–19096; AD 2017–23–02]
DC 20590.
the procedures and tests identified as RC can FOR FURTHER INFORMATION CONTACT:
be done and the airplane can be put back in RIN 2120–AA64 Jennifer Tsakoumakis, Aerospace
an airworthy condition. Any substitutions or Engineer, Airframe Section, FAA, Los
changes to procedures or tests identified as Airworthiness Directives; The Boeing
Angeles ACO Branch, 3960 Paramount
RC require approval of an AMOC. Company Airplanes
Boulevard, Lakewood, CA 90712–4137;
(l) Related Information AGENCY: Federal Aviation phone: 562–627–5264; fax: 562–627–
(1) Refer to Mandatory Continuing Administration (FAA), DOT. 5210; email: Jennifer.Tsakoumakis@
Airworthiness Information (MCAI) EASA AD ACTION: Final rule. faa.gov.
2017–0023, dated February 10, 2017, for
SUPPLEMENTARY INFORMATION:
related information. This MCAI may be SUMMARY: We are adopting a new
found in the AD docket on the Internet at airworthiness directive (AD) for certain Discussion
http://www.regulations.gov by searching for The Boeing Company Model 737–200,
and locating Docket No. FAA–2017–0710. We issued a notice of proposed
–200C, –300, –400, and –500 series rulemaking (NPRM) to amend 14 CFR
(2) For more information about this AD,
contact Dan Rodina, Aerospace Engineer, airplanes. This AD was prompted by an part 39 by adding an AD that would
International Section, Transport Standards evaluation by the design approval apply to certain The Boeing Company
Branch, FAA, 1601 Lind Avenue SW., holder (DAH) indicating that the Model 737–200, –200C, –300, –400, and
Renton, WA 98057–3356; telephone 425– fuselage crown skin panels are subject –500 series airplanes. The NPRM
227–2125; fax 425–227–1149. to widespread fatigue damage (WFD). published in the Federal Register on
(3) Service information identified in this This AD requires repetitive inspections, August 10, 2017 (82 FR 37366). The
AD that is not incorporated by reference is replacement, and applicable on-
available at the addresses specified in NPRM was prompted by an evaluation
condition actions for certain fuselage by the DAH indicating that the fuselage
paragraphs (m)(3) and (m)(4) of this AD.
crown skin panels. We are issuing this crown skin panels are subject to WFD.
(m) Material Incorporated by Reference AD to address the unsafe condition on The NPRM proposed to require
(1) The Director of the Federal Register these products. repetitive inspections, replacement, and
approved the incorporation by reference DATES: This AD is effective December applicable on-condition actions for
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(IBR) of the service information listed in this 20, 2017. certain fuselage crown skin panels.
paragraph under 5 U.S.C. 552(a) and 1 CFR The Director of the Federal Register We are issuing this AD to detect and
part 51. approved the incorporation by reference
(2) You must use this service information
correct cracking in the fuselage crown
of a certain publication listed in this AD skin panels. Multiple adjacent cracks in
as applicable to do the actions required by
this AD, unless this AD specifies otherwise. as of December 20, 2017. the fuselage crown skin could link up
(i) Airbus Service Bulletin A300–57–6118, ADDRESSES: For service information and lead to decompression or loss of
Revision 01, dated January 31, 2017. identified in this final rule, contact structural integrity of the airplane.
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Document Created: 2018-10-25 10:36:23
Document Modified: 2018-10-25 10:36:23
| 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 is effective December 20, 2017. | |
| Contact | Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227- 1149. | |
| FR Citation | 82 FR 52832 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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