80 FR 44832 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 144 (July 28, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 144 (July 28, 2015)
| Page Range | 44832-44835 | |
| FR Document | 2015-18156 |
[Federal Register Volume 80, Number 144 (Tuesday, July 28, 2015)] [Rules and Regulations] [Pages 44832-44835] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-18156] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2014-0778; Directorate Identifier 2014-NM-095-AD; Amendment 39-18220; AD 2015-15-11] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. This AD was prompted by reports of skin cracks and subsequent findings of hidden corrosion found on the mating surfaces between certain skin and stringers at circumferential skin splices. This AD requires general visual inspections of the fuselage skin at certain lower circumferential splices for the presence of existing external doublers, repetitive inspections of the fuselage skin, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct hidden corrosion due to compromised fillet seals, which can result in skin cracking and consequent loss of capability to support limit loads. DATES: This AD is effective September 1, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 1, 2015. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544- 5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-0778. 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-2014- 0778; 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 (phone: 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: Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6432; fax: 425-917-6590; email: [email protected]. 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 The Boeing Company Model 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. The NPRM published in the Federal Register on November 28, 2014 (79 FR 70799). The NPRM was prompted by reports of skin cracks and subsequent findings of hidden corrosion found on the mating surfaces between certain skin and stringers at circumferential skin splices. The NPRM proposed to require general visual inspections of the fuselage skin at certain lower circumferential splices for the presence of existing external doublers, repetitive inspections of the fuselage skin, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct hidden corrosion due to compromised fillet seals, which can result in skin cracking and consequent loss of capability to support limit loads. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 70799, November 28, 2014) and the FAA's response to each comment. Concurrence With NPRM (79 FR 70799, November 28, 2014) United Airlines stated that it concurs with the proposed requirements specified in the NPRM (79 FR 70799, November 28, 2014). [[Page 44833]] Request To Clarify What Prompted the AD Action and Clarify the Unsafe Condition Boeing requested that we clarify the unsafe condition and revise various locations of the NPRM (79 FR 70799, November 28, 2014) to indicate that corrosion was discovered only after a skin crack was reported. Boeing explained the hidden corrosion between the skin and stringer was not visibly detectable and was discovered only after a skin crack was reported. We agree to revise the sentences that specify the unsafe condition and that specify what prompted the AD action. We have revised the SUMMARY of this final rule, as well as the Discussion and paragraph (e) of this AD, by adding the phrase ``hidden corrosion due to'' to the sentences that specify the unsafe condition, and by adding the phrase ``skin cracks and subsequent findings of hidden'' to the sentences that discuss what prompted the AD action. Request To Clarify Requirements Based on Presence of Doubler Repair Boeing requested that we revise paragraph (g) of the NPRM (79 FR 70799, November 28, 2014) to clarify the proposed requirements for surface low frequency eddy current (LFEC) inspections for areas with and without repair doublers. We agree to revise paragraph (g) of this AD to clarify configurations of areas with and without repair doublers. We have revised paragraph (g)(1) and added new paragraph (g)(2) to this AD to specify configurations having ``an external repair doubler'' and where ``no existing repair doubler'' exists. Request To Add Required High Frequency Eddy Current (HFEC) Inspections Boeing requested that we revise paragraphs (g)(2) and (h)(2)(i) of the NPRM (79 FR 70799, November 28, 2014) by adding HFEC inspections as a required action. We disagree with specifying HFEC inspections as requested in this AD because this AD already requires compliance with all applicable ``related investigative actions,'' which include applicable HFEC inspections. The terminology for the proposed AD requirements was addressed by the NPRM (79 FR 70799, November 28, 2014). Our standard practice is to specify actions that are related to the primary action and actions that further investigate the nature of any condition found as ``related investigative actions.'' No change has been made to this AD in this regard. Request To Reference Correct Service Information UPS requested that the correct eddy current inspection procedure be referenced in the NPRM (79 FR 70799, November 28, 2014). UPS stated that Boeing Information Notice 747-53A2861 IN 01, dated April 24, 2014, was issued to inform operators that Paragraph 3.B, Part 2, Step 1, of the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2861, dated April 1, 2014, should refer to ``747 Nondestructive test (NDT) Manual Part 6, 53-30-00, Procedure 5,'' instead of ``747 NDT Manual Part 6, 51-00-00, Procedure 8,'' as the correct inspection procedure of the fuselage skin. UPS stated that adding this information would prevent the need for requests for alternative methods of compliance (AMOCs) related to this error. We find that clarification is needed. To clarify this information, we have added a new exception to include the correct source of service information for this inspection. New paragraph (i)(3) of this AD refers to ``747 NDT Manual Part 6, 53-30-00, Procedure 5,'' as the appropriate source of service information for the eddy current inspection of the fuselage skin. We have also added a reference to paragraph (i)(3) of this AD in paragraphs (g) and (h) of this AD. Request To Exclude Location From Required Inspections UPS requested that the NPRM (79 FR 70799, November 28, 2014) be revised to exclude a certain location from the inspection requirements, or that the proposed AD provide an inspection procedure that is adequate for that location. UPS stated that Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014, specifies that external surface LFEC inspections for corrosion of the fuselage skin be done using ``747 NDT Manual Part 6, 51-00-00, Procedure 5 or Procedure 12,'' which are appropriate for skins with a specified thickness. UPS stated Table 2 of Appendix C of Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014, contains an error. Skin panels having part number 65B23792-XX are chem milled with a thickness that exceeds the specification listed in Table 2 of Appendix C of Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014. Therefore, the NDT procedures are not valid for those skin panels at this location. UPS stated that since action is identified as ``Required for Compliance,'' by Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014, no deviations are allowed without AMOC approval. We disagree with the request. Agreeing with the request would delay the issuance of the AD and we find that delaying this action would be inappropriate in light of the identified unsafe condition. Boeing is aware of the discrepancy with the NDI instructions, and is actively working on a global AMOC for operators to correct the error by means of a validated procedure. Operators have the option of proposing their own procedure in accordance with paragraph (j) of this AD. Since chem milling affects the ability to accomplish Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014, and the corrective action is not clear in the service information, we have added an exception to new paragraph (i)(4) of this AD to specify where Paragraph 3.B, Part 3, Step 1, of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014, specifies doing external surface LFEC inspections in accordance with ``747 NDT Manual Part 6, 51-00-00, Procedure 5 or Procedure 12,'' and the skin panels are chem milled with a thickness that exceeds the specification listed in Table 2 of Appendix C of Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014, this AD requires using an AMOC per paragraph (j) of this AD. We have added a reference to paragraph (i)(4) of this AD in paragraphs (g) and (h) of this AD. Operators may request approval of an AMOC under the provisions of paragraph (j) of this AD, for procedures that would help them meet the NDT test requirements. 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 (79 FR 70799, November 28, 2014) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 70799, November 28, 2014). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 747-53A2861, dated April 1, [[Page 44834]] 2014. The service information describes procedures for inspections of the fuselage skin at certain lower circumferential splices for the presence of existing external doublers, inspections of the fuselage skin for cracking and corrosion, and corrective actions. 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 of this final rule. Costs of Compliance We estimate that this AD affects 165 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspection...................... Up to 121 work- $0 Up to $10,285...... Up to $1,697,025. hours x $85 per hour = $10,285. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable 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 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 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): 2015-15-11 The Boeing Company: Amendment 39-18220; Docket No. FAA- 2014-0778; Directorate Identifier 2014-NM-095-AD. (a) Effective Date This AD is effective September 1, 2015. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747- 400F, 747SR, and 747SP series airplanes; certificated in any category, as identified in Boeing Alert Service Bulletin 747- 53A2861, dated April 1, 2014. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of skin cracks and subsequent findings of hidden corrosion found on the mating surfaces between certain skin and stringers at circumferential skin splices. We are issuing this AD to detect and correct hidden corrosion due to compromised fillet seals, which can result in skin cracking and consequent loss of capability to support limit loads. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections and Repair for Group 1 Airplanes For airplanes identified as Group 1 in Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014: At the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014, except as provided by paragraph (i)(1) of this AD, do external general visual inspections for the presence of external doublers on the fuselage skin, and do the applicable actions specified in paragraphs (g)(1) and (g)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014, except as required by paragraphs (i)(2), (i)(3), and (i)(4) of this AD. Do all applicable repetitive inspections of the fuselage skin thereafter at the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014. (1) For each affected area with an external repair doubler: Before further flight, do a surface low frequency eddy current (LFEC) inspection for skin cracks of the external lower lobe repair doubler, and do all applicable related investigative and corrective actions. Do all applicable related investigative and corrective actions before further flight. (2) For any affected area with no external repair doubler: Before further flight, do a surface LFEC inspection for corrosion of the external lower lobe skin surface, and do all applicable related investigative and corrective actions. Do all applicable related investigative and corrective actions before further flight. (h) Inspections and Repair for Group 2 Airplanes For airplanes identified as Group 2 in Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014: At the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014, except as provided by paragraph (i)(1) of this AD, do external general visual inspections for the presence of [[Page 44835]] external doublers on the fuselage skin, and do the applicable actions specified in paragraphs (h)(1) and (h)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014, except as required by paragraphs (i)(2), (i)(3), and (i)(4) of this AD. (1) For affected areas with any existing repair doubler: Before further flight, do inspections and applicable repairs using a method approved in accordance with the procedures specified by paragraph (j) of this AD. (2) For affected areas with no existing repair doubler, do the applicable actions specified in paragraph (h)(2)(i) and (h)(2)(ii) of this AD. (i) Before further flight, do a surface LFEC inspection for corrosion of the external lower lobe doubler, a surface LFEC inspection for skin cracks of the external lower lobe doubler, a detailed inspection for cracks of the external lower lobe skin, and do all applicable related investigative and corrective actions. Do all applicable related investigative and corrective actions before further flight. (ii) Do all applicable repetitive inspections of the fuselage skin thereafter at the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014. (i) Exceptions to Service Information Specifications (1) Where Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014, specifies a compliance time ``after the original issue date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Although Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014, specifies to contact Boeing for repair data, and specifies that action as ``RC'' (Required for Compliance), this AD requires repair before further flight using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (3) Where Paragraph 3.B, Part 2, Step 1, of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014, incorrectly identifies ``747 NDT Manual Part 6, 51- 00-00, Procedure 8,'' associated with the LFEC inspection for skin cracks of the external lower lobe repair doubler, the correct reference is ``747 NDT Manual Part 6, 53-30-00, Procedure 5.'' (4) Where Paragraph 3.B, Part 3, Step 1, of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014, specifies doing external surface LFEC inspections in accordance with ``747 NDT Manual Part 6, 51-00-00, Procedure 5 or Procedure 12,'' and the skin panels are chem milled with a thickness that exceeds the specification listed in Table 2 of Appendix C of Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014, this AD requires using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), 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 manager of the ACO, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: [email protected]. (2) 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. (3) Except as required by paragraph (i) of this AD: Some steps in the Work Instructions are labeled as Required for Compliance (RC). If this service bulletin is mandated by an AD, then the steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. Steps not labeled 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 RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (4) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (k) Related Information For more information about this AD, contact Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057- 3356; phone: 425-917-6432; fax: 425-917-6590; email: [email protected]. (l) 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 the AD specifies otherwise. (i) Boeing Alert Service Bulletin 747-53A2861, dated April 1, 2014. (ii) Reserved. (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544- 5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. (4) You may view this service information at FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on July 16, 2015. Suzanne Masterson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-18156 Filed 7-27-15; 8:45 am] BILLING CODE 4910-13-P
![44832 Federal Register / Vol. 80, No. 144 / Tuesday, July 28, 2015 / Rules and Regulations
Internet at http://www.regulations.gov by DEPARTMENT OF TRANSPORTATION www.regulations.gov by searching for
searching for and locating Docket No. FAA– and locating Docket No. FAA–2014–
2015–2463. Federal Aviation Administration 0778; or in person at the Docket
(2) Service information identified in this Management Facility between 9 a.m.
AD that is not incorporated by reference is 14 CFR Part 39 and 5 p.m., Monday through Friday,
available at the addresses specified in except Federal holidays. The AD docket
[Docket No. FAA–2014–0778; Directorate
paragraphs (k)(4) and (k)(6) of this AD. contains this AD, the regulatory
Identifier 2014–NM–095–AD; Amendment
(k) Material Incorporated by Reference 39–18220; AD 2015–15–11] evaluation, any comments received, and
other information. The address for the
(1) The Director of the Federal Register RIN 2120–AA64
Docket Office (phone: 800–647–5527) is
approved the incorporation by reference
Airworthiness Directives; The Boeing Docket Management Facility, U.S.
(IBR) of the service information listed in this
Company Airplanes Department of Transportation, Docket
paragraph under 5 U.S.C. 552(a) and 1 CFR
Operations, M–30, West Building
part 51.
AGENCY: Federal Aviation Ground Floor, Room W12–140, 1200
(2) You must use this service information
Administration (FAA), DOT. New Jersey Avenue SE., Washington,
as applicable to do the actions required by
this AD, unless this AD specifies otherwise. ACTION: Final rule. DC 20590.
(3) The following service information was FOR FURTHER INFORMATION CONTACT: Bill
SUMMARY: We are adopting a new Ashforth, Aerospace Engineer, Airframe
approved for IBR on July 14, 2015 (80 FR
32449, June 9, 2015).
airworthiness directive (AD) for certain Branch, ANM–120S, FAA, Seattle
(i) Bombardier Service Bulletin 84–29–34,
The Boeing Company Model 747–100B, Aircraft Certification Office (ACO), 1601
dated May 9, 2013.
747–100B SUD, 747–200B, 747–200C, Lind Avenue SW., Renton, WA 98057–
(ii) Parker Service Bulletin 82910012–29– 747–200F, 747–300, 747–400, 747– 3356; phone: 425–917–6432; fax: 425–
431, dated October 22, 2012. 400D, 747–400F, 747SR, and 747SP 917–6590; email: bill.ashforth@faa.gov.
(4) For Bombardier service information series airplanes. This AD was prompted
SUPPLEMENTARY INFORMATION:
identified in this AD, contact Bombardier, by reports of skin cracks and subsequent
Inc., Q-Series Technical Help Desk, 123 findings of hidden corrosion found on Discussion
Garratt Boulevard, Toronto, Ontario M3K the mating surfaces between certain skin
We issued a notice of proposed
1Y5, Canada; telephone 416–375–4000; fax and stringers at circumferential skin
rulemaking (NPRM) to amend 14 CFR
416–375–4539; email thd.qseries@ splices. This AD requires general visual
part 39 by adding an AD that would
aero.bombardier.com; Internet http:// inspections of the fuselage skin at
apply to certain The Boeing Company
www.bombardier.com. certain lower circumferential splices for
Model 747–100B, 747–100B SUD, 747–
(5) For Parker service information the presence of existing external
200B, 747–200C, 747–200F, 747–300,
identified in this AD, contact Parker doublers, repetitive inspections of the
747–400, 747–400D, 747–400F, 747SR,
Aerospace, 14300 Alton Parkway, Irvine, CA fuselage skin, and related investigative
and 747SP series airplanes. The NPRM
92618; phone: 949–833–3000; Internet: and corrective actions if necessary. We
published in the Federal Register on
http://www.parker.com. are issuing this AD to detect and correct
November 28, 2014 (79 FR 70799). The
(6) You may view this service information hidden corrosion due to compromised
NPRM was prompted by reports of skin
at the FAA, Transport Airplane Directorate, fillet seals, which can result in skin
cracks and subsequent findings of
1601 Lind Avenue SW., Renton, WA. For cracking and consequent loss of
hidden corrosion found on the mating
information on the availability of this capability to support limit loads.
surfaces between certain skin and
material at the FAA, call 425–227–1221. DATES: This AD is effective September 1, stringers at circumferential skin splices.
(7) You may view this service information 2015. The NPRM proposed to require general
that is incorporated by reference at the The Director of the Federal Register visual inspections of the fuselage skin at
National Archives and Records approved the incorporation by reference certain lower circumferential splices for
Administration (NARA). For information on of a certain publication listed in this AD
the availability of this material at NARA, call
the presence of existing external
as of September 1, 2015. doublers, repetitive inspections of the
202–741–6030, or go to: http://
ADDRESSES: For service information fuselage skin, and related investigative
www.archives.gov/federal-register/cfr/ibr-
locations.html.
identified in this AD, contact Boeing and corrective actions if necessary. We
Commercial Airplanes, Attention: Data are issuing this AD to detect and correct
& Services Management, P.O. Box 3707, hidden corrosion due to compromised
Issued in Renton, Washington, on July 13, MC 2H–65, Seattle, WA 98124–2207; fillet seals, which can result in skin
2015. telephone 206–544–5000, extension 1; cracking and consequent loss of
Jeffrey E. Duven, fax 206–766–5680; Internet https:// capability to support limit loads.
Manager, Transport Airplane Directorate, www.myboeingfleet.com.You may view
Aircraft Certification Service. this referenced service information at Comments
[FR Doc. 2015–17975 Filed 7–27–15; 8:45 am] the FAA, Transport Airplane We gave the public the opportunity to
BILLING CODE 4910–13–P Directorate, participate in developing this AD. The
1601 Lind Avenue SW., Renton, WA. following presents the comments
For information on the availability of received on the NPRM (79 FR 70799,
this material at the FAA, call 425–227– November 28, 2014) and the FAA’s
asabaliauskas on DSK5VPTVN1PROD with RULES
1221. It is also available on the Internet response to each comment.
at http://www.regulations.gov by
Concurrence With NPRM (79 FR 70799,
searching for and locating Docket No.
November 28, 2014)
FAA–2014–0778.
United Airlines stated that it concurs
Examining the AD Docket with the proposed requirements
You may examine the AD docket on specified in the NPRM (79 FR 70799,
the Internet at http:// November 28, 2014).
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![44834 Federal Register / Vol. 80, No. 144 / Tuesday, July 28, 2015 / Rules and Regulations
2014. The service information describes actions. This service information is Costs of Compliance
procedures for inspections of the reasonably available because the
fuselage skin at certain lower interested parties have access to it We estimate that this AD affects 165
circumferential splices for the presence through their normal course of business airplanes of U.S. registry.
of existing external doublers, or by the means identified in the We estimate the following costs to
inspections of the fuselage skin for ADDRESSES section of this final rule. comply with this AD:
cracking and corrosion, and corrective
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspection ............................... Up to 121 work-hours × $85 $0 Up to $10,285 ........................ Up to $1,697,025.
per hour = $10,285.
We have received no definitive data under the criteria of the Regulatory which can result in skin cracking and
that would enable us to provide cost Flexibility Act. consequent loss of capability to support limit
estimates for the on-condition actions loads.
List of Subjects in 14 CFR Part 39
specified in this AD. (f) Compliance
Air transportation, Aircraft, Aviation
Authority for This Rulemaking Comply with this AD within the
safety, Incorporation by reference, compliance times specified, unless already
Title 49 of the United States Code Safety. done.
specifies the FAA’s authority to issue Adoption of the Amendment (g) Inspections and Repair for Group 1
rules on aviation safety. Subtitle I, Airplanes
section 106, describes the authority of Accordingly, under the authority
delegated to me by the Administrator, For airplanes identified as Group 1 in
the FAA Administrator. Subtitle VII: Boeing Alert Service Bulletin 747–53A2861,
Aviation Programs, describes in more the FAA amends 14 CFR part 39 as
follows: dated April 1, 2014: At the applicable times
detail the scope of the Agency’s specified in paragraph 1.E., ‘‘Compliance,’’ of
authority. PART 39—AIRWORTHINESS Boeing Alert Service Bulletin 747–53A2861,
We are issuing this rulemaking under dated April 1, 2014, except as provided by
DIRECTIVES
the authority described in Subtitle VII, paragraph (i)(1) of this AD, do external
Part A, Subpart III, Section 44701: ■ 1. The authority citation for part 39 general visual inspections for the presence of
external doublers on the fuselage skin, and
‘‘General requirements.’’ Under that continues to read as follows: do the applicable actions specified in
section, Congress charges the FAA with Authority: 49 U.S.C. 106(g), 40113, 44701. paragraphs (g)(1) and (g)(2) of this AD, in
promoting safe flight of civil aircraft in accordance with the Accomplishment
air commerce by prescribing regulations § 39.13 [Amended] Instructions of Boeing Alert Service Bulletin
for practices, methods, and procedures ■ 2. The FAA amends § 39.13 by adding 747–53A2861, dated April 1, 2014, except as
the Administrator finds necessary for the following new airworthiness required by paragraphs (i)(2), (i)(3), and (i)(4)
safety in air commerce. This regulation directive (AD): of this AD. Do all applicable repetitive
is within the scope of that authority inspections of the fuselage skin thereafter at
2015–15–11 The Boeing Company: the applicable times specified in paragraph
because it addresses an unsafe condition Amendment 39–18220; Docket No. 1.E., ‘‘Compliance,’’ of Boeing Alert Service
that is likely to exist or develop on FAA–2014–0778; Directorate Identifier Bulletin 747–53A2861, dated April 1, 2014.
products identified in this rulemaking 2014–NM–095–AD. (1) For each affected area with an external
action. repair doubler: Before further flight, do a
(a) Effective Date
surface low frequency eddy current (LFEC)
Regulatory Findings This AD is effective September 1, 2015. inspection for skin cracks of the external
This AD will not have federalism (b) Affected ADs lower lobe repair doubler, and do all
implications under Executive Order applicable related investigative and
None.
13132. This AD will not have a corrective actions. Do all applicable related
(c) Applicability investigative and corrective actions before
substantial direct effect on the States, on
This AD applies to The Boeing Company further flight.
the relationship between the national (2) For any affected area with no external
government and the States, or on the Model 747–100B, 747–100B SUD, 747–200B,
747–200C, 747–200F, 747–300, 747–400, repair doubler: Before further flight, do a
distribution of power and 747–400D, 747–400F, 747SR, and 747SP surface LFEC inspection for corrosion of the
responsibilities among the various series airplanes; certificated in any category, external lower lobe skin surface, and do all
levels of government. as identified in Boeing Alert Service Bulletin applicable related investigative and
For the reasons discussed above, I 747–53A2861, dated April 1, 2014. corrective actions. Do all applicable related
certify that this AD: investigative and corrective actions before
(d) Subject further flight.
(1) Is not a ‘‘significant regulatory
Air Transport Association (ATA) of (h) Inspections and Repair for Group 2
action’’ under Executive Order 12866, America Code 53, Fuselage.
Airplanes
asabaliauskas on DSK5VPTVN1PROD with RULES
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures (e) Unsafe Condition For airplanes identified as Group 2 in
(44 FR 11034, February 26, 1979), This AD was prompted by reports of skin Boeing Alert Service Bulletin 747–53A2861,
cracks and subsequent findings of hidden dated April 1, 2014: At the applicable times
(3) Will not affect intrastate aviation
corrosion found on the mating surfaces specified in paragraph 1.E., ‘‘Compliance,’’ of
in Alaska, and between certain skin and stringers at Boeing Alert Service Bulletin 747–53A2861,
(4) Will not have a significant circumferential skin splices. We are issuing dated April 1, 2014, except as provided by
economic impact, positive or negative, this AD to detect and correct hidden paragraph (i)(1) of this AD, do external
on a substantial number of small entities corrosion due to compromised fillet seals, general visual inspections for the presence of
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![Federal Register / Vol. 80, No. 144 / Tuesday, July 28, 2015 / Rules and Regulations 44835
external doublers on the fuselage skin, and (j) Alternative Methods of Compliance (4) You may view this service information
do the applicable actions specified in (AMOCs) at FAA, Transport Airplane Directorate, 1601
paragraphs (h)(1) and (h)(2) of this AD, in (1) The Manager, Seattle Aircraft Lind Avenue SW., Renton, WA. For
accordance with the Accomplishment Certification Office (ACO), FAA, has the information on the availability of this
Instructions of Boeing Alert Service Bulletin authority to approve AMOCs for this AD, if material at the FAA, call 425–227–1221.
747–53A2861, dated April 1, 2014, except as requested using the procedures found in 14 (5) You may view this service information
required by paragraphs (i)(2), (i)(3), and (i)(4) CFR 39.19. In accordance with 14 CFR 39.19, that is incorporated by reference at the
of this AD. send your request to your principal inspector National Archives and Records
or local Flight Standards District Office, as Administration (NARA). For information on
(1) For affected areas with any existing
appropriate. If sending information directly the availability of this material at NARA, call
repair doubler: Before further flight, do
to the manager of the ACO, send it to the 202–741–6030, or go to: http://
inspections and applicable repairs using a www.archives.gov/federal-register/cfr/ibr-
method approved in accordance with the attention of the person identified in
paragraph (k) of this AD. Information may be locations.html.
procedures specified by paragraph (j) of this
AD. emailed to: 9-ANM-Seattle-ACO-AMOC- Issued in Renton, Washington, on July 16,
(2) For affected areas with no existing Requests@faa.gov. 2015.
(2) Before using any approved AMOC, Suzanne Masterson,
repair doubler, do the applicable actions
notify your appropriate principal inspector,
specified in paragraph (h)(2)(i) and (h)(2)(ii) Acting Manager, Transport Airplane
or lacking a principal inspector, the manager
of this AD. Directorate, Aircraft Certification Service.
of the local Flight Standards District Office/
(i) Before further flight, do a surface LFEC certificate holding district office. [FR Doc. 2015–18156 Filed 7–27–15; 8:45 am]
inspection for corrosion of the external lower (3) Except as required by paragraph (i) of BILLING CODE 4910–13–P
lobe doubler, a surface LFEC inspection for this AD: Some steps in the Work Instructions
skin cracks of the external lower lobe are labeled as Required for Compliance (RC).
doubler, a detailed inspection for cracks of If this service bulletin is mandated by an AD, DEPARTMENT OF TRANSPORTATION
the external lower lobe skin, and do all then the steps labeled as RC, including
applicable related investigative and substeps under an RC step and any figures Federal Aviation Administration
corrective actions. Do all applicable related identified in an RC step, must be done to
investigative and corrective actions before comply with the AD. An AMOC is required
14 CFR Part 39
further flight. for any deviations to RC steps, including
(ii) Do all applicable repetitive inspections substeps and identified figures. Steps not [Docket No. FAA–2014–0921; Directorate
of the fuselage skin thereafter at the labeled as RC may be deviated from using Identifier 2014–NM–073–AD; Amendment
applicable times specified in paragraph 1.E., accepted methods in accordance with the 39–18193; AD 2015–13–06]
‘‘Compliance,’’ of Boeing Alert Service operator’s maintenance or inspection
program without obtaining approval of an RIN 2120–AA64
Bulletin 747–53A2861, dated April 1, 2014.
AMOC, provided the RC steps, including
(i) Exceptions to Service Information substeps and identified figures, can still be Airworthiness Directives; The Boeing
Specifications done as specified, and the airplane can be Company Airplanes
(1) Where Boeing Alert Service Bulletin put back in an airworthy condition.
(4) An AMOC that provides an acceptable AGENCY: Federal Aviation
747–53A2861, dated April 1, 2014, specifies Administration (FAA), DOT.
level of safety may be used for any repair
a compliance time ‘‘after the original issue
required by this AD if it is approved by the ACTION: Final rule.
date of this service bulletin,’’ this AD Boeing Commercial Airplanes Organization
requires compliance within the specified Designation Authorization (ODA) that has SUMMARY: We are superseding
compliance time after the effective date of been authorized by the Manager, Seattle Airworthiness Directive (AD) 2013–14–
this AD. ACO, to make those findings. For a repair 05 for certain The Boeing Company
(2) Although Boeing Alert Service Bulletin method to be approved, the repair must meet Model 747–400 and 747–400F series
747–53A2861, dated April 1, 2014, specifies the certification basis of the airplane, and the
to contact Boeing for repair data, and airplanes. AD 2013–14–05 required
approval must specifically refer to this AD.
specifies that action as ‘‘RC’’ (Required for repetitive inspections of the longeron
Compliance), this AD requires repair before (k) Related Information extension fittings for cracking, and
further flight using a method approved in For more information about this AD, related investigative and corrective
accordance with the procedures specified in contact Bill Ashforth, Aerospace Engineer, actions if necessary. This new AD
paragraph (j) of this AD. Airframe Branch, ANM–120S, FAA, Seattle would continue to require the actions
(3) Where Paragraph 3.B, Part 2, Step 1, of Aircraft Certification Office (ACO), 1601 Lind specified in AD 2013–14–05, and would
the Accomplishment Instructions of Boeing Avenue SW., Renton, WA 98057–3356; add new repetitive high frequency eddy
Alert Service Bulletin 747–53A2861, dated phone: 425–917–6432; fax: 425–917–6590;
email: bill.ashforth@faa.gov.
current (HFEC) inspections of any
April 1, 2014, incorrectly identifies ‘‘747 modified, repaired, or replaced longeron
NDT Manual Part 6, 51–00–00, Procedure 8,’’ (l) Material Incorporated by Reference extension fitting for cracking, and
associated with the LFEC inspection for skin
cracks of the external lower lobe repair
(1) The Director of the Federal Register applicable related investigative and
approved the incorporation by reference corrective actions if necessary. This AD
doubler, the correct reference is ‘‘747 NDT
(IBR) of the service information listed in this was prompted by reports of cracking in
Manual Part 6, 53–30–00, Procedure 5.’’
paragraph under 5 U.S.C. 552(a) and 1 CFR the outboard flange of the longeron
(4) Where Paragraph 3.B, Part 3, Step 1, of part 51.
the Accomplishment Instructions of Boeing (2) You must use this service information
extension fittings, and our
Alert Service Bulletin 747–53A2861, dated as applicable to do the actions required by determination that more work is
April 1, 2014, specifies doing external this AD, unless the AD specifies otherwise. necessary on airplanes on which a
surface LFEC inspections in accordance with (i) Boeing Alert Service Bulletin 747– permanent repair, longeron extension
asabaliauskas on DSK5VPTVN1PROD with RULES
‘‘747 NDT Manual Part 6, 51–00–00, 53A2861, dated April 1, 2014. fitting replacement, or modification was
Procedure 5 or Procedure 12,’’ and the skin (ii) Reserved. accomplished. We are issuing this AD to
panels are chem milled with a thickness that (3) For service information identified in detect and correct cracks in the longeron
exceeds the specification listed in Table 2 of this AD, contact Boeing Commercial extension fittings, which can become
Appendix C of Boeing Alert Service Bulletin Airplanes, Attention: Data & Services
747–53A2861, dated April 1, 2014, this AD large and adversely affect the structural
Management, P.O. Box 3707, MC 2H–65,
requires using a method approved in Seattle, WA 98124–2207; telephone 206– integrity of the airplane.
accordance with the procedures specified in 544–5000, extension 1; fax 206–766–5680; DATES: This AD is effective September 1,
paragraph (j) of this AD. Internet https://www.myboeingfleet.com. 2015.
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Document Created: 2018-02-23 09:28:26
Document Modified: 2018-02-23 09:28:26
| 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 September 1, 2015. | |
| Contact | Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6432; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 80 FR 44832 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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