81 FR 91695 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 243 (December 19, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 243 (December 19, 2016)
| Page Range | 91695-91698 | |
| FR Document | 2016-29511 |
[Federal Register Volume 81, Number 243 (Monday, December 19, 2016)] [Rules and Regulations] [Pages 91695-91698] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-29511] [[Page 91695]] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-7425; Directorate Identifier 2014-NM-244-AD; Amendment 39-18741; AD 2016-25-15] 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) 2011-17-05, for certain Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4- 103, A300 B4-203, and A300 B4-2C airplanes. AD 2011-17-05 required repetitive inspections in sections 13 through 18 of the fuselage between rivets of the longitudinal lap joints between frames (FRs) 18 and 80 for cracking, and repair or modification if necessary. This new AD requires a revised repetitive inspection program of all longitudinal lap joints and repairs between FRs 18 and 80 to address widespread fatigue damage (WFD). This AD was prompted by an evaluation done by the design approval holder indicating that certain sections of the longitudinal lap joints are subject to WFD; therefore, a revised inspection program is necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 23, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 16, 2011 (76 FR 63177, October 12, 2011). ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 7425. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 7425; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800- 647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 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 2011-17-05, Amendment 39-16769 (76 FR 63177, October 12, 2011) (``AD 2011-17-05''). AD 2011-17-05 applied to certain Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4-103, A300 B4-203, and A300 B4-2C airplanes. The NPRM published in the Federal Register on July 7, 2016 (81 FR 44232). The NPRM was prompted by an evaluation done by the design approval holder indicating that certain sections of the longitudinal lap joints are subject to WFD. The NPRM proposed to continue to require repetitive inspections in sections 13 through 18 of the fuselage between rivets of the longitudinal lap joints between FRs 18 and 80 for cracking, and repair or modification if necessary. The NPRM also proposed to require a revised repetitive inspection program of all longitudinal lap joints and repairs between FRs 18 and 80 to address this WFD. We are issuing this AD to detect and correct fatigue cracking of the longitudinal lap joints of the fuselage, which could result in reduced structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2014-0265, dated December 9, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states: Cracks were found on in-service aeroplanes in sections 13 to 18 of the fuselage between rivets of longitudinal lap joints between frames (FR) 18 and FR80. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. To address this unsafe condition, Airbus developed an inspection programme for the longitudinal lap joints and repairs between FR18 and FR80, and EASA issued AD 2007-0091 [which corresponds to FAA AD 2011-17-05] to require the implementation of that programme. Since EASA AD 2007-0091 was issued, [a] new Widespread Fatigue Damage regulation has been issued. This new regulation led to the revision of the maintenance programme for the longitudinal lap joints and repairs between FR18 and FR80. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2007-0091, which is superseded, and requires implementation of the revised inspection programme. Required actions include repetitive inspections of the bonded inner doublers of the longitudinal lap joints in sections 13 through 18 for disbonding or corrosion, and repairing any disbonding and corrosion; a follow-on rototest or ultrasonic inspection to verify cracking, and repair of any cracking. The repetitive inspection interval ranges from 3,000 flight cycles up to 8,000 flight cycles, depending on airplane configuration. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA-2016-7425. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data 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. Costs of Compliance We estimate that this AD affects 4 airplanes of U.S. registry. [[Page 91696]] Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost product operators ---------------------------------------------------------------------------------------------------------------- Retained actions from AD 2011-17-05........... 3,735 work-hours x $85 per hour $317,475 $1,269,900 = $317,475. New inspections............................... 140 work-hours x $85 per hour = $11,900 $47,600 $11,900. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that enables us to provide cost estimates for the 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. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2011-17-05, Amendment 39-16769 (76 FR 63177, October 12, 2011), and adding the following new AD: 2016-25-15 Airbus: Amendment 39-18741; Docket No. FAA-2016-7425; Directorate Identifier 2014-NM-244-AD. (a) Effective Date This AD is effective January 23, 2017. (b) Affected ADs This AD replaces AD 2011-17-05, Amendment 39-16769 (76 FR 63177, October 12, 2011) (``AD 2011-17-05''). (c) Applicability This AD applies to Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4-103, A300 B4-203, and A300 B4-2C airplanes; certificated in any category; all manufacturer serial numbers, except those on which Airbus Modification 2611 has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by an evaluation done by the design approval holder indicating that certain sections of the longitudinal lap joints are subject to widespread fatigue damage. We are issuing this AD to detect and correct fatigue cracking of the longitudinal lap joints of the fuselage, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Fuselage Inner Doubler Inspections and Repair, With Revised Formatting This paragraph restates the requirements of paragraph (l) of AD 2011-17-05, with revised formatting. For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in sections 13 through 18 (except sections 16 and 17 at stringer 31 left-hand and right-hand) for disbonding and cracking have not been done as of November 16, 2011 (the effective date of AD 2011-17-05), as specified by Airbus Service Bulletin A300-53-229: Prior to the accumulation of 24,000 total flight cycles or within 15 years since new, whichever occurs first; or within 60 days after November 16, 2011; whichever occurs later; do a detailed inspection of the fuselage bonded inner doublers of the longitudinal lap joints in sections 13 through 18 (except sections 16 and 17 at stringer 31 left-hand and right-hand) for disbonding and cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and no cracking are found, repeat the inspection thereafter at the applicable intervals specified in paragraph (h) of this AD. (1) If no cracking is found, and ``minor'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22. (2) If no cracking is found, and ``major'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (h) Retained Repetitive Intervals for Inspections for Disbonding and Cracking, With No Changes This paragraph restates the repetitive intervals specified in table 1 of AD 2011-17-05, with no changes. At the applicable time specified in paragraph (h)(1) or (h)(2) of this AD, repeat the inspection required by paragraph (g) of this AD. (1) For sections 13 and 14 as specified in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997: Repeat the inspection at intervals not to exceed 7 years or 12,000 flight cycles, whichever occurs first. (2) For sections 15 through 18 as specified in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997: Repeat the inspection within 8.5 years or 12,000 flight cycles, whichever occurs first. [[Page 91697]] (i) Retained Fuselage Inner Doubler Inspections and Repair, With No Changes This paragraph restates the requirements of paragraph (m) of AD 2011-17-05, with no changes. For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in sections 13 through 18 (except sections 16 and 17 at stringer 31 left-hand and right-hand) for disbonding and cracking have been done as of November 16, 2011 (the effective date of AD 2011-17-05), as specified in Airbus Service Bulletin A300-53-229; except for airplanes on which a repair of that area has been done as specified in Airbus Service Bulletin A300-53-229: Within 7 years or 12,000 flight cycles (for sections 13 and 14), or within 8.5 years or 12,000 flight cycles (for sections 15 and 18), after doing the inspection, whichever occurs first; or within 60 days after November 16, 2011, whichever occurs later, do a detailed inspection of the fuselage bonded inner doublers of the longitudinal lap joints in sections 13 through 18 (except sections 16 and 17 at stringer 31 left-hand and right-hand) for disbonding and cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and no cracking are found, repeat the inspection at the applicable time specified in paragraph (h) of this AD. (1) If no cracking is found, and ``minor'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22. (2) If no cracking is found, and ``major'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (j) Retained Fuselage Inner Doubler Inspections and Repair, With No Changes This paragraph restates the requirements of paragraph (n) of AD 2011-17-05, with no changes. For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in sections 16 and 17 at stringer 31 left-hand and right-hand for disbonding and cracking have not been done as of November 16, 2011 (the effective date of AD 2011-17-05), as specified in Airbus Service Bulletin A300-53-229: Prior to the accumulation of 24,000 total flight cycles or within 12 years since new, whichever occurs first; or within 60 days after November 16, 2011, whichever occurs later, do a detailed inspection of the fuselage bonded inner doublers of the longitudinal lap joints in sections 16 and 17 at stringer 31 left-hand and right-hand for disbonding and cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and no cracking are found, repeat the inspection thereafter at intervals not to exceed 7 years or 12,000 flight cycles, whichever occurs first. (1) If no cracking is found, and ``minor'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22. Doing a repair in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, terminates the repetitive inspections required by this paragraph for that area. (2) If no cracking is found, and ``major'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (k) Retained Fuselage Inner Doubler Inspections and Repair, With No Changes This paragraph restates the requirements of paragraph (o) of AD 2011-17-05, with no changes. For airplanes on which any inspections of the fuselage bonded inner doublers of the longitudinal lap joints in sections 16 and 17 at stringer 31 left-hand and right-hand for disbonding and cracking have been done as of November 16, 2011, as specified in Airbus Service Bulletin A300-53-229; except airplanes on which a repair of that area has been done as specified in Airbus Service Bulletin A300-53-229: Within 7 years or 12,000 flight cycles after doing the inspection, whichever occurs first; or within 60 days after November 16, 2011; whichever occurs later; do a detailed inspection of the fuselage bonded inner doublers of the longitudinal lap joints in sections 16 and 17 at stringer 31 left-hand and right- hand for disbonding and cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and no corrosion are found, repeat the inspection thereafter at intervals not to exceed 7 years or 12,000 flight cycles, whichever occurs first. (1) If no cracking is found, and ``minor'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Repeat the inspection thereafter at intervals not to exceed 1 year for areas below stringer 22, and at intervals not to exceed 2 years for areas above and including stringer 22. Doing a repair, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, terminates the repetitive inspections required by this paragraph for that area. (2) If no cracking is found, and ``major'' disbonding, as defined in Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, is found: Within 1,000 flight cycles after doing the inspection, repair, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (3) If any cracking is found, repair prior to further flight, in accordance with Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997. (l) New Repetitive Inspections and Repair Within 180 days after the effective date of this AD, do rototest and ultrasonic inspections, as applicable, for cracking of all longitudinal lap joints and repairs between frames 18 and 80; and repair any cracking before further flight; using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). Repeat the applicable inspection, including post-repair inspections, thereafter at intervals approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. Accomplishing the initial inspection and applicable repairs required by this paragraph terminates the actions required by paragraphs (g) through (k) of this AD. (m) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-2125; fax 425-227-1149. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (n) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2014-0265, dated December 9, 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- 2016-7425. [[Page 91698]] (o) 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 November 16, 2011 (76 FR 63177, October 12, 2011). (i) Airbus Service Bulletin A300-53-229, Revision 5, dated April 8, 1997, including Appendix A300SB/53-229, dated April 10, 1989. Only pages 1, 2, 5, 11, and 12 of Airbus Service Bulletin A300-53- 229, Revision 5, dated April 8, 1997, show revision level 5 and issue date April 8, 1997; pages 3, 4-10, and 13-17 show revision level 4 and issue date March 30, 1994; and pages 1-17 of Appendix A300SB/53-229 show issue date April 10, 1989. (ii) Reserved. (4) 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. (5) 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. (6) 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 December 1, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-29511 Filed 12-16-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 243 / Monday, December 19, 2016 / Rules and Regulations 91695
DEPARTMENT OF TRANSPORTATION Examining the AD Docket MCAI’’), to correct an unsafe condition
You may examine the AD docket on for the specified products.
Federal Aviation Administration the Internet at http:// The MCAI states:
www.regulations.gov by searching for Cracks were found on in-service aeroplanes
14 CFR Part 39 and locating Docket No. FAA–2016– in sections 13 to 18 of the fuselage between
[Docket No. FAA–2016–7425; Directorate 7425; or in person at the Docket rivets of longitudinal lap joints between
Identifier 2014–NM–244–AD; Amendment Management Facility between 9 a.m. frames (FR) 18 and FR80.
39–18741; AD 2016–25–15] and 5 p.m., Monday through Friday, This condition, if not detected and
corrected, could affect the structural integrity
RIN 2120–AA64 except Federal holidays. The AD docket of the aeroplane.
contains this AD, the regulatory To address this unsafe condition, Airbus
Airworthiness Directives; Airbus evaluation, any comments received, and developed an inspection programme for the
Airplanes other information. The address for the longitudinal lap joints and repairs between
Docket Office (telephone 800–647–5527) FR18 and FR80, and EASA issued AD 2007–
AGENCY: Federal Aviation is Docket Management Facility, U.S. 0091 [which corresponds to FAA AD 2011–
Administration (FAA), Department of Department of Transportation, Docket 17–05] to require the implementation of that
Transportation (DOT). Operations, M–30, West Building programme.
ACTION: Final rule. Ground Floor, Room W12–140, 1200 Since EASA AD 2007–0091 was issued, [a]
new Widespread Fatigue Damage regulation
New Jersey Avenue SE., Washington, has been issued. This new regulation led to
SUMMARY: We are superseding DC 20590.
Airworthiness Directive (AD) 2011–17– the revision of the maintenance programme
FOR FURTHER INFORMATION CONTACT: Dan for the longitudinal lap joints and repairs
05, for certain Airbus Model A300 B2–
Rodina, Aerospace Engineer, between FR18 and FR80.
1C, A300 B2–203, A300 B2K–3C, A300– For the reasons described above, this
International Branch, ANM–116,
B4–103, A300 B4–203, and A300 B4–2C [EASA] AD retains the requirements of EASA
Transport Airplane Directorate, FAA,
airplanes. AD 2011–17–05 required AD 2007–0091, which is superseded, and
1601 Lind Avenue SW., Renton, WA
repetitive inspections in sections 13 requires implementation of the revised
98057–3356; telephone 425–227–2125;
through 18 of the fuselage between inspection programme.
fax 425–227–1149.
rivets of the longitudinal lap joints Required actions include repetitive
SUPPLEMENTARY INFORMATION:
between frames (FRs) 18 and 80 for inspections of the bonded inner
cracking, and repair or modification if Discussion doublers of the longitudinal lap joints in
necessary. This new AD requires a sections 13 through 18 for disbonding or
We issued a notice of proposed
revised repetitive inspection program of corrosion, and repairing any disbonding
rulemaking (NPRM) to amend 14 CFR
all longitudinal lap joints and repairs and corrosion; a follow-on rototest or
part 39 to supersede AD 2011–17–05,
between FRs 18 and 80 to address ultrasonic inspection to verify cracking,
Amendment 39–16769 (76 FR 63177,
widespread fatigue damage (WFD). This and repair of any cracking. The
October 12, 2011) (‘‘AD 2011–17–05’’).
AD was prompted by an evaluation repetitive inspection interval ranges
AD 2011–17–05 applied to certain
done by the design approval holder from 3,000 flight cycles up to 8,000
Airbus Model A300 B2–1C, A300 B2–
indicating that certain sections of the flight cycles, depending on airplane
203, A300 B2K–3C, A300–B4–103, A300
longitudinal lap joints are subject to configuration. You may examine the
B4–203, and A300 B4–2C airplanes. The
WFD; therefore, a revised inspection MCAI in the AD docket on the Internet
NPRM published in the Federal
program is necessary. We are issuing at http://www.regulations.gov by
Register on July 7, 2016 (81 FR 44232).
this AD to address the unsafe condition searching for and locating it in Docket
The NPRM was prompted by an
on these products. No. FAA–2016–7425.
evaluation done by the design approval
DATES: This AD is effective January 23, holder indicating that certain sections of
2017. Comments
the longitudinal lap joints are subject to
The Director of the Federal Register WFD. The NPRM proposed to continue We gave the public the opportunity to
approved the incorporation by reference to require repetitive inspections in participate in developing this AD. We
of a certain publication listed in this AD sections 13 through 18 of the fuselage received no comments on the NPRM or
as of November 16, 2011 (76 FR 63177, between rivets of the longitudinal lap on the determination of the cost to the
October 12, 2011). joints between FRs 18 and 80 for public.
ADDRESSES: For service information cracking, and repair or modification if Conclusion
identified in this final rule, contact necessary. The NPRM also proposed to
Airbus SAS, Airworthiness Office— require a revised repetitive inspection We reviewed the available data and
EAW, 1 Rond Point Maurice Bellonte, program of all longitudinal lap joints determined that air safety and the
31707 Blagnac Cedex, France; telephone and repairs between FRs 18 and 80 to public interest require adopting this AD
+33 5 61 93 36 96; fax +33 5 61 93 44 address this WFD. We are issuing this as proposed, except for minor editorial
51; email account.airworth-eas@ AD to detect and correct fatigue changes. We have determined that these
airbus.com; Internet http:// cracking of the longitudinal lap joints of minor changes:
www.airbus.com. You may view this the fuselage, which could result in • Are consistent with the intent that
referenced service information at the reduced structural integrity of the was proposed in the NPRM for
FAA, Transport Airplane Directorate, airplane. correcting the unsafe condition; and
1601 Lind Avenue SW., Renton, WA. The European Aviation Safety Agency • Do not add any additional burden
srobinson on DSK5SPTVN1PROD with RULES
For information on the availability of (EASA), which is the Technical Agent upon the public than was already
this material at the FAA, call 425–227– for the Member States of the European proposed in the NPRM.
1221. It is also available on the Internet Union, has issued EASA AD 2014–0265,
Costs of Compliance
at http://www.regulations.gov by dated December 9, 2014 (referred to
searching for and locating Docket No. after this as the Mandatory Continuing We estimate that this AD affects 4
FAA–2016–7425. Airworthiness Information, or ‘‘the airplanes of U.S. registry.
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![91696 Federal Register / Vol. 81, No. 243 / Monday, December 19, 2016 / Rules and Regulations
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost product operators
Retained actions from AD 2011–17–05 ...... 3,735 work-hours × $85 per hour = $317,475 .............................. $317,475 $1,269,900
New inspections .......................................... 140 work-hours × $85 per hour = $11,900 ................................... $11,900 $47,600
We have received no definitive data Adoption of the Amendment formatting. For airplanes on which any
that enables us to provide cost estimates inspections of the fuselage bonded inner
Accordingly, under the authority doublers of the longitudinal lap joints in
for the on-condition actions specified in delegated to me by the Administrator,
this AD. sections 13 through 18 (except sections 16
the FAA amends 14 CFR part 39 as and 17 at stringer 31 left-hand and right-
Authority for This Rulemaking follows: hand) for disbonding and cracking have not
been done as of November 16, 2011 (the
Title 49 of the United States Code PART 39—AIRWORTHINESS effective date of AD 2011–17–05), as
specifies the FAA’s authority to issue DIRECTIVES specified by Airbus Service Bulletin A300–
rules on aviation safety. Subtitle I, 53–229: Prior to the accumulation of 24,000
section 106, describes the authority of ■ 1. The authority citation for part 39 total flight cycles or within 15 years since
the FAA Administrator. ‘‘Subtitle VII: continues to read as follows: new, whichever occurs first; or within 60
Aviation Programs,’’ describes in more Authority: 49 U.S.C. 106(g), 40113, 44701. days after November 16, 2011; whichever
detail the scope of the Agency’s occurs later; do a detailed inspection of the
authority. § 39.13 [Amended] fuselage bonded inner doublers of the
longitudinal lap joints in sections 13 through
We are issuing this rulemaking under ■ 2. The FAA amends § 39.13 by 18 (except sections 16 and 17 at stringer 31
the authority described in ‘‘Subtitle VII, removing Airworthiness Directive (AD) left-hand and right-hand) for disbonding and
Part A, Subpart III, Section 44701: 2011–17–05, Amendment 39–16769 (76 cracking, in accordance with the
General requirements.’’ Under that FR 63177, October 12, 2011), and Accomplishment Instructions of Airbus
section, Congress charges the FAA with adding the following new AD: Service Bulletin A300–53–229, Revision 5,
promoting safe flight of civil aircraft in 2016–25–15 Airbus: Amendment 39–18741; dated April 8, 1997. If no disbonding and no
air commerce by prescribing regulations Docket No. FAA–2016–7425; Directorate cracking are found, repeat the inspection
for practices, methods, and procedures Identifier 2014–NM–244–AD. thereafter at the applicable intervals specified
in paragraph (h) of this AD.
the Administrator finds necessary for (a) Effective Date (1) If no cracking is found, and ‘‘minor’’
safety in air commerce. This regulation disbonding, as defined in Airbus Service
This AD is effective January 23, 2017.
is within the scope of that authority Bulletin A300–53–229, Revision 5, dated
because it addresses an unsafe condition (b) Affected ADs April 8, 1997, is found: Repeat the inspection
that is likely to exist or develop on This AD replaces AD 2011–17–05, thereafter at intervals not to exceed 1 year for
products identified in this rulemaking Amendment 39–16769 (76 FR 63177, October areas below stringer 22, and at intervals not
action. 12, 2011) (‘‘AD 2011–17–05’’). to exceed 2 years for areas above and
including stringer 22.
Regulatory Findings (c) Applicability
(2) If no cracking is found, and ‘‘major’’
This AD applies to Airbus Model A300 B2– disbonding, as defined in Airbus Service
We determined that this AD will not 1C, A300 B2–203, A300 B2K–3C, A300–B4– Bulletin A300–53–229, Revision 5, dated
have federalism implications under 103, A300 B4–203, and A300 B4–2C April 8, 1997, is found: Within 1,000 flight
Executive Order 13132. This AD will airplanes; certificated in any category; all cycles after doing the inspection, repair, in
not have a substantial direct effect on manufacturer serial numbers, except those on accordance with the Accomplishment
the States, on the relationship between which Airbus Modification 2611 has been Instructions of Airbus Service Bulletin A300–
the national government and the States, embodied in production. 53–229, Revision 5, dated April 8, 1997.
or on the distribution of power and (d) Subject (3) If any cracking is found, repair prior to
responsibilities among the various further flight, in accordance with Airbus
Air Transport Association (ATA) of
levels of government. Service Bulletin A300–53–229, Revision 5,
America Code 53, Fuselage.
dated April 8, 1997.
For the reasons discussed above, I (e) Reason
certify that this AD: (h) Retained Repetitive Intervals for
This AD was prompted by an evaluation Inspections for Disbonding and Cracking,
1. Is not a ‘‘significant regulatory done by the design approval holder
action’’ under Executive Order 12866; With No Changes
indicating that certain sections of the
2. Is not a ‘‘significant rule’’ under the longitudinal lap joints are subject to This paragraph restates the repetitive
DOT Regulatory Policies and Procedures widespread fatigue damage. We are issuing intervals specified in table 1 of AD 2011–17–
this AD to detect and correct fatigue cracking 05, with no changes. At the applicable time
(44 FR 11034, February 26, 1979); specified in paragraph (h)(1) or (h)(2) of this
3. Will not affect intrastate aviation in of the longitudinal lap joints of the fuselage,
which could result in reduced structural AD, repeat the inspection required by
Alaska; and integrity of the airplane. paragraph (g) of this AD.
4. Will not have a significant (1) For sections 13 and 14 as specified in
economic impact, positive or negative, (f) Compliance Airbus Service Bulletin A300–53–229,
on a substantial number of small entities Comply with this AD within the Revision 5, dated April 8, 1997: Repeat the
srobinson on DSK5SPTVN1PROD with RULES
under the criteria of the Regulatory compliance times specified, unless already inspection at intervals not to exceed 7 years
done. or 12,000 flight cycles, whichever occurs
Flexibility Act.
first.
(g) Retained Fuselage Inner Doubler (2) For sections 15 through 18 as specified
List of Subjects in 14 CFR Part 39
Inspections and Repair, With Revised in Airbus Service Bulletin A300–53–229,
Air transportation, Aircraft, Aviation Formatting Revision 5, dated April 8, 1997: Repeat the
safety, Incorporation by reference, This paragraph restates the requirements of inspection within 8.5 years or 12,000 flight
Safety. paragraph (l) of AD 2011–17–05, with revised cycles, whichever occurs first.
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![91698 Federal Register / Vol. 81, No. 243 / Monday, December 19, 2016 / Rules and Regulations
(o) Material Incorporated by Reference Minimums and Obstacle Departure 25082, Oklahoma City, OK 73125)
(1) The Director of the Federal Register Procedures (ODPs) for operations at Telephone: (405) 954–4164.
approved the incorporation by reference certain airports. These regulatory SUPPLEMENTARY INFORMATION: This rule
(IBR) of the service information listed in this actions are needed because of the amends Title 14 of the Code of Federal
paragraph under 5 U.S.C. 552(a) and 1 CFR adoption of new or revised criteria, or Regulations, Part 97 (14 CFR part 97), by
part 51. because of changes occurring in the establishing, amending, suspending, or
(2) You must use this service information
as applicable to do the actions required by
National Airspace System, such as the removes SIAPS, Takeoff Minimums
this AD, unless this AD specifies otherwise. commissioning of new navigational and/or ODPS. The complete regulatory
(3) The following service information was facilities, adding new obstacles, or description of each SIAP and its
approved for IBR on November 16, 2011 (76 changing air traffic requirements. These associated Takeoff Minimums or ODP
FR 63177, October 12, 2011). changes are designed to provide safe for an identified airport is listed on FAA
(i) Airbus Service Bulletin A300–53–229, and efficient use of the navigable form documents which are incorporated
Revision 5, dated April 8, 1997, including airspace and to promote safe flight by reference in this amendment under 5
Appendix A300SB/53–229, dated April 10, operations under instrument flight rules U.S.C. 552(a), 1 CFR part 51, and 14
1989. Only pages 1, 2, 5, 11, and 12 of Airbus
Service Bulletin A300–53–229, Revision 5,
at the affected airports. CFR part § 97.20. The applicable FAA
dated April 8, 1997, show revision level 5 DATES: This rule is effective December forms are FAA Forms 8260–3, 8260–4,
and issue date April 8, 1997; pages 3, 4–10, 19, 2016. The compliance date for each 8260–5, 8260–15A, and 8260–15B when
and 13–17 show revision level 4 and issue SIAP, associated Takeoff Minimums, required by an entry on 8260–15A.
date March 30, 1994; and pages 1–17 of and ODP is specified in the amendatory The large number of SIAPs, Takeoff
Appendix A300SB/53–229 show issue date provisions. Minimums and ODPs, their complex
April 10, 1989. The incorporation by reference of nature, and the need for a special format
(ii) Reserved. make publication in the Federal
(4) For service information identified in
certain publications listed in the
regulations is approved by the Director Register expensive and impractical.
this AD, contact Airbus SAS, Airworthiness Further, airmen do not use the
Office—EAW, 1 Rond Point Maurice of the Federal Register as of December
Bellonte, 31707 Blagnac Cedex, France; 19, 2016. regulatory text of the SIAPs, Takeoff
telephone +33 5 61 93 36 96; fax +33 5 61 Minimums or ODPs, but instead refer to
ADDRESSES: Availability of matters
93 44 51; email account.airworth-eas@ their graphic depiction on charts
incorporated by reference in the
airbus.com; Internet http://www.airbus.com. printed by publishers of aeronautical
amendment is as follows:
(5) You may view this service information materials. Thus, the advantages of
at the FAA, Transport Airplane Directorate, For Examination incorporation by reference are realized
1601 Lind Avenue SW., Renton, WA. For and publication of the complete
information on the availability of this 1. U.S. Department of Transportation,
Docket Ops-M30, 1200 New Jersey description of each SIAP, Takeoff
material at the FAA, call 425–227–1221.
Avenue SE., West Bldg., Ground Floor, Minimums and ODP listed on FAA form
(6) You may view this service information
that is incorporated by reference at the Washington, DC 20590–0001. documents is unnecessary. This
National Archives and Records 2. The FAA Air Traffic Organization amendment provides the affected CFR
Administration (NARA). For information on Service Area in which the affected sections and specifies the types of
the availability of this material at NARA, call airport is located; SIAPs, Takeoff Minimums and ODPs
202–741–6030, or go to: http://
3. The office of Aeronautical with their applicable effective dates.
www.archives.gov/federal-register/cfr/ibr- This amendment also identifies the
locations.html. Navigation Products, 6500 South
MacArthur Blvd., Oklahoma City, OK airport and its location, the procedure,
Issued in Renton, Washington, on 73169 or, and the amendment number.
December 1, 2016.
4. The National Archives and Records Availability and Summary of Material
Michael Kaszycki, Administration (NARA). For Incorporated by Reference
Acting Manager, Transport Airplane information on the availability of this
Directorate, Aircraft Certification Service. The material incorporated by
material at NARA, call 202–741–6030, reference is publicly available as listed
[FR Doc. 2016–29511 Filed 12–16–16; 8:45 am] or go to: http://www.archives.gov/ in the ADDRESSES section.
BILLING CODE 4910–13–P federal_register/code_of_federal_ The material incorporated by
regulations/ibr_locations.html. reference describes SIAPS, Takeoff
DEPARTMENT OF TRANSPORTATION Availability Minimums and/or ODPS as identified in
the amendatory language for part 97 of
All SIAPs and Takeoff Minimums and
Federal Aviation Administration this final rule.
ODPs are available online free of charge.
Visit the National Flight Data Center at The Rule
14 CFR Part 97 nfdc.faa.gov to register. Additionally, This amendment to 14 CFR part 97 is
[Docket No. 31107; Amdt. No. 3723] individual SIAP and Takeoff Minimums effective upon publication of each
and ODP copies may be obtained from separate SIAP, Takeoff Minimums and
Standard Instrument Approach the FAA Air Traffic Organization ODP as Amended in the transmittal.
Procedures, and Takeoff Minimums Service Area in which the affected Some SIAP and Takeoff Minimums and
and Obstacle Departure Procedures; airport is located. textual ODP amendments may have
Miscellaneous Amendments FOR FURTHER INFORMATION CONTACT: been issued previously by the FAA in a
AGENCY: Federal Aviation Thomas J. Nichols, Flight Procedure Flight Data Center (FDC) Notice to
srobinson on DSK5SPTVN1PROD with RULES
Administration (FAA), DOT. Standards Branch (AFS–420), Flight Airmen (NOTAM) as an emergency
ACTION: Final rule. Technologies and Programs Divisions, action of immediate flight safety relating
Flight Standards Service, Federal directly to published aeronautical
SUMMARY: This rule establishes, amends, Aviation Administration, Mike charts.
suspends, or removes Standard Monroney Aeronautical Center, 6500 The circumstances that created the
Instrument Approach Procedures South MacArthur Blvd. Oklahoma City, need for some SIAP and Takeoff
(SIAPs) and associated Takeoff OK 73169 (Mail Address: P.O. Box Minimums and ODP amendments may
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Document Created: 2016-12-17 03:15:49
Document Modified: 2016-12-17 03:15:49
| 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 January 23, 2017. | |
| 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 91695 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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