80 FR 39394 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 131 (July 9, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 131 (July 9, 2015)
| Page Range | 39394-39397 | |
| FR Document | 2015-16763 |
[Federal Register Volume 80, Number 131 (Thursday, July 9, 2015)] [Proposed Rules] [Pages 39394-39397] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-16763] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-2460; Directorate Identifier 2014-NM-163-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2010-26- 10, which applies to certain The Boeing Company Model 747-200C, -200F, -400, -400D, and -400F series airplanes. AD 2010-26-10 currently requires repetitive inspections for cracking of the lap joints, modification of certain lap joints, and certain post-repair inspections of the lap joints. Since we issued AD 2010-26-10, an evaluation by the design approval holder (DAH) has indicated that certain lap joints are subject to widespread fatigue damage (WFD). This proposed AD would add new repetitive post-modification inspections for cracking in the lap joints, and repair if necessary. We are proposing this AD to detect and correct fatigue cracking in certain lap joints, which could result in rapid depressurization and consequent reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by August 24, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed 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-2015-2460. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 2460; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office [[Page 39395]] (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax: 425-917-6590; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-2460; Directorate Identifier 2014-NM-163-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On December 13, 2010, we issued AD 2010-26-10, Amendment 39-16549 (75 FR 81427, December 28, 2010), for certain Model 747-200C, -200F, - 400, -400D, and -400F series airplanes. AD 2010-26-10 requires repetitive inspections for cracking of the lap joints, modification of certain lap joints and certain post-repair inspections of the lap joints. AD 2010-26-10 resulted from a structural review of affected skin lap joints for WFD. We issued AD 2010-26-10 to prevent fatigue cracking in certain lap joints, which could result in rapid depressurization and consequent reduced structural integrity of the airplane. Widespread Fatigue Damage Structural fatigue damage is progressive. It begins as minute cracks, and those cracks grow under the action of repeated stresses. This can happen because of normal operational conditions and design attributes, or because of isolated situations or incidents such as material defects, poor fabrication quality, or corrosion pits, dings, or scratches. Fatigue damage can occur locally, in small areas or structural design details, or globally. Global fatigue damage is general degradation of large areas of structure with similar structural details and stress levels. Multiple-site damage is global damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Global damage can also occur in multiple elements such as adjacent frames or stringers. Multiple- site-damage and multiple-element-damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane, in a condition known as widespread fatigue damage (WFD). As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA's WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. Actions Since AD 2010-26-10, Amendment 39-16549 (75 FR 81427, December 28, 2010), Was Issued Since we issued AD 2010-26-10, Amendment 39-16549 (75 FR 81427, December 28, 2010), an evaluation by the DAH has indicated that certain lap joints are subject to WFD. Related Service Information Under 1 CFR part 51 We reviewed Boeing Alert Service Bulletin 747-53A2499, Revision 3, dated July 15, 2014. The service information describes procedures for body skin lap joint inspections and modifications in sections 41, 42, and 43. 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 NPRM. FAA's Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements Although this proposed AD does not explicitly restate the requirements of AD 2010-26-10, Amendment 39-16549 (75 FR 81427, December 28, 2010), this proposed AD would retain all of the requirements of AD 2010-26-10. Those requirements are referenced in the service information identified previously, which, in turn, is referenced in paragraphs (g) and (h) of this proposed AD. This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ``Difference Between this Proposed AD and the Service Bulletin.'' Refer to this service information for details on the procedures and compliance times. Difference Between This Proposed AD and the Service Bulletin Although Boeing Alert Service Bulletin 747-53A2499, Revision 3, dated July 15, 2014, specifies that operators may contact the manufacturer for disposition of certain repair conditions, this proposed AD would require repairing those conditions in one of the following ways: In accordance with a method that we approve; or Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization [[Page 39396]] Designation Authorization (ODA) whom we have authorized to make those findings. Explanation of Compliance Time The compliance time for the modification specified in this proposed AD for addressing WFD was established to ensure that discrepant structure is modified before WFD develops in airplanes. Standard inspection techniques cannot be relied on to detect WFD before it becomes a hazard to flight. We will not grant any extensions of the compliance time to complete any AD-mandated service bulletin related to WFD without extensive new data that would substantiate and clearly warrant such an extension. Costs of Compliance We estimate that this proposed AD affects 120 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Pre-modification inspections Up to 675 work- $0 Up to $57,375 per Up to $6,885,000 [retained action from AD 2010-26- hours, = up to inspection cycle. per inspection 10, Amendment 39-16549 (75 FR $57,375. cycle. 81427, December 28, 2010)]. Modification [retained action Up to 5,819 work- 0 Up to $494,615..... Up to $59,353,800. from AD 2010-26-10, Amendment 39- hours x $85 per 16549 (75 FR 81427, December 28, hour = up to 2010)]. $494,615. New proposed post-modification Up to 105 work- 0 Up to $8,925 per Up to $1,071,000 inspections. hours x $85 per inspection cycle. per inspection hour = up to cycle. $8,925. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide a cost estimate for the on-condition actions specified in this proposed 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 have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed regulation: (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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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) 2010-26-10, Amendment 39-16549 (75 FR 81427, December 28, 2010), and adding the following new AD: The Boeing Company: Docket No. FAA-2015-2460; Directorate Identifier 2014-NM-163-AD. (a) Comments Due Date The FAA must receive comments on this AD action by August 24, 2015. (b) Affected ADs This AD replaces AD 2010-26-10, Amendment 39-16549 (75 FR 81427, December 28, 2010). (c) Applicability This AD applies to The Boeing Company Model 747-200C, -200F, - 400, -400D, and -400F series airplanes; certificated in any category; as identified in Boeing Alert Service Bulletin 747- 53A2499, Revision 3, dated July 15, 2014. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain lap joints are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking in certain lap joints, which could result in rapid depressurization and consequent reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Lap Joint Inspections At the applicable time specified in Table 1 and Table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2499, Revision 3, dated July 15, 2014, except as required by paragraph (j)(1) of this AD: Do eddy current inspections for cracks in the skin of the lap joints, and do all applicable repairs, in accordance with the Accomplishment Instructions of Boeing [[Page 39397]] Alert Service Bulletin 747-53A2499, Revision 3, dated July 15, 2014, except as required by paragraph (j)(2) of this AD. Do all applicable repairs before further flight. Repeat the applicable inspections thereafter at intervals not to exceed those specified in Table 1 and Table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2499, Revision 3, dated July 15, 2014 (h) Lap Joint Modification At the applicable time specified in Tables 2, 4, 5, and 6 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2499, Revision 3, dated July 15, 2014, except as required by paragraph (j)(1) of this AD: Modify the applicable lap joints, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2499, Revision 3, dated July 15, 2014, except as required by paragraph (j)(2) of this AD. Accomplishment of the modification required by this paragraph terminates the repetitive inspections required by paragraph (g) of this AD for the length of the modified lap joint. (i) Lap Joint Post-Modification Inspections At the applicable time specified in Tables 7, 8, 9, and 10 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2499, Revision 3, dated July 15, 2014, except as required by paragraph (j)(1) of this AD: Do the applicable inspections specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2499, Revision 3, dated July 15, 2014. Repeat the applicable inspections thereafter at the applicable times specified in Tables 7, 8, 9, and 10 of paragraph 1.E, ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2499, Revision 3, dated July 15, 2014. If any crack is found during any inspection, repair before further flight using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (1) For airplanes identified as Groups 2 through 5 and 8 through 10 in Boeing Alert Service Bulletin 747-53A2499, Revision 3, dated July 15, 2014: Internal detailed and surface high frequency eddy current (HFEC) inspections for any crack in the skin or internal doubler. (2) For airplanes identified as Groups 6, 11, and 19 in Boeing Alert Service Bulletin 747-53A2499, Revision 3, dated July 15, 2014: External detailed and low frequency eddy current inspections of the upper and lower skin panels for cracking, external detailed and HFEC inspections of the doubler for cracking, and internal detailed and HFEC inspections of the upper and lower skin panels for cracking (for airplanes with a stringer 6 lap joint modification installed between STA 340 and STA 400 as specified in Boeing Service Bulletin 747-53-2272); or internal detailed and surface HFEC inspections for any crack in the skin or internal doubler (for airplanes with lap joints modified as specified in Boeing Alert Service Bulletin 747- 53A2499.) (3) For airplanes identified as Groups 1, 7, and 12 through 18 in Boeing Alert Service Bulletin 747-53A2499, Revision 3, dated July 15, 2014: Internal detailed and surface HFEC inspections for any crack in the skin or internal doubler. (j) Exceptions to Service Bulletin Procedures (1) Where Boeing Alert Service Bulletin 747-53A2499, Revision 3, dated July 15, 2014, specifies a compliance time ``after the Revision 3 date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where Boeing Alert Service Bulletin 747-53A2499, Revision 3, dated July 15, 2014, specifies to contact Boeing for repair instructions: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (k) Credit for Previous Actions Actions done before the effective date of this AD using the service information identified in paragraph (k)(1) or (k)(2) of this AD are acceptable for compliance with the corresponding requirements of paragraphs (g) and (h) of this AD. (1) Boeing Alert Service Bulletin 747-53A2499, Revision 1, dated October 30, 2008, which is not incorporated by reference in this AD. (2) Boeing Alert Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010, which was incorporated by reference in AD 2010-26- 10, Amendment 39-16549 (75 FR 81427, December 28, 2010). (l) 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 (m)(1) 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) 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. (4) AMOCs approved for AD 2010-26-10, Amendment 39-16549 (75 FR 81427, December 28, 2010), are approved as AMOCs for the corresponding provisions of paragraphs (g) and (h) this AD. (m) Related Information (1) For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax: 425-917-6590; email: [email protected]. (2) 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, Washington. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on June 29, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-16763 Filed 7-8-15; 8:45 am] BILLING CODE 4910-13-P
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(a) Comments Due Date (ii) Steps not labeled as RC may be cracking of the lap joints, modification
We must receive comments by August 24, deviated from using accepted methods in of certain lap joints, and certain post-
2015. accordance with the operator’s maintenance repair inspections of the lap joints.
or inspection program without obtaining
(b) Affected ADs Since we issued AD 2010–26–10, an
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can evaluation by the design approval
None.
still be done as specified, and the airplane holder (DAH) has indicated that certain
(c) Applicability can be put back in an airworthy condition. lap joints are subject to widespread
This AD applies to The Boeing Company (4) An AMOC that provides an acceptable fatigue damage (WFD). This proposed
Model 777–200, –200LR, –300, –300ER, and level of safety may be used for any repair AD would add new repetitive post-
777F series airplanes, certificated in any required by this AD if it is approved by the modification inspections for cracking in
category, as identified in Boeing Special Boeing Commercial Airplanes Organization the lap joints, and repair if necessary.
Attention Service Bulletin 777–54–0035, Designation Authorization (ODA) that has We are proposing this AD to detect and
dated October 30, 2014. been authorized by the Manager, Seattle
correct fatigue cracking in certain lap
ACO, to make those findings. For a repair
(d) Subject
method to be approved, the repair must meet joints, which could result in rapid
Air Transport Association (ATA) of the certification basis of the airplane, and the depressurization and consequent
America Code 54, Nacelles/Pylons. approval must specifically refer to this AD. reduced structural integrity of the
(e) Unsafe Condition
airplane.
(i) Related Information
This AD was prompted by reports of fire DATES: We must receive comments on
(1) For more information about this AD,
and smoke at the engine aft pylon area contact Kevin Nguyen, Aerospace Engineer, this proposed AD by August 24, 2015.
resulting from fuel leakage caused by a Propulsion Branch, ANM–140S, FAA, Seattle ADDRESSES: You may send comments,
damaged O-ring in the fuel coupling attached Aircraft Certification Office (ACO), 1601 Lind using the procedures found in 14 CFR
to the wing front spar. We are issuing this AD Avenue SW., Renton, WA 98057–3356; 11.43 and 11.45, by any of the following
to prevent fire and smoke at the engine aft phone: 425–917–6501; fax: 425–917–6590; methods:
pylon area in the event of a fuel leak, which
could cause personal injury during ground
email: kevin.nguyen@faa.gov. • Federal eRulemaking Portal: Go to
(2) For service information identified in http://www.regulations.gov. Follow the
operations. A fire spreading back and up to this AD, contact Boeing Commercial
the aft fairing pylon can result in an instructions for submitting comments.
Airplanes, Attention: Data & Services
uncontrolled fire in the strut and ignite the Management, P.O. Box 3707, MC 2H–65,
• Fax: 202–493–2251.
fuel tank. Seattle, WA 98124–2207; telephone 206– • Mail: U.S. Department of
544–5000, extension 1; fax 206–766–5680; Transportation, Docket Operations,
(f) Compliance
Internet https://www.myboeingfleet.com. You M–30, West Building Ground Floor,
Comply with this AD within the may view this referenced service information Room W12–140, 1200 New Jersey
compliance times specified, unless already
at the FAA, Transport Airplane Directorate, Avenue SE., Washington, DC 20590.
done.
1601 Lind Avenue SW., Renton, WA. For • Hand Delivery: Deliver to Mail
(g) Sealant Application information on the availability of this address above between 9 a.m. and 5
Within 1,875 days after the effective date material at the FAA, call 425–227–1221. p.m., Monday through Friday, except
of this AD, apply sealant to fill the gap Issued in Renton, Washington, on June 30, Federal holidays.
between the lower wing panels adjacent to 2015. For service information identified in
the strut aft vapor barrier, in accordance with Michael Kaszycki, this proposed AD, contact Boeing
the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777–54–
Acting Manager, Transport Airplane Commercial Airplanes, Attention: Data
Directorate, Aircraft Certification Service. & Services Management, P.O. Box 3707,
0035, dated October 30, 2014.
[FR Doc. 2015–16766 Filed 7–8–15; 8:45 am] MC 2H–65, Seattle, WA 98124–2207;
(h) Alternative Methods of Compliance telephone 206–544–5000, extension 1;
BILLING CODE 4910–13–P
(AMOCs) fax 206–766–5680; Internet https://
(1) The Manager, Seattle Aircraft www.myboeingfleet.com. You may view
Certification Office (ACO), FAA, has the DEPARTMENT OF TRANSPORTATION this referenced service information at
authority to approve AMOCs for this AD, if
the FAA, Transport Airplane
requested using the procedures found in 14 Federal Aviation Administration
CFR 39.19. In accordance with 14 CFR 39.19, Directorate, 1601 Lind Avenue SW.,
send your request to your principal inspector Renton, WA. For information on the
or local Flight Standards District Office, as 14 CFR Part 39 availability of this material at the FAA,
appropriate. If sending information directly [Docket No. FAA–2015–2460; Directorate call 425–227–1221. It is also available
to the manager of the ACO, send it to the Identifier 2014–NM–163–AD] on the Internet at http://
attention of the person identified in www.regulations.gov by searching for
paragraph (i)(1) of this AD. Information may RIN 2120–AA64
and locating Docket No. FAA–2015–
be emailed to: 9-ANM-Seattle-ACO-AMOC-
Airworthiness Directives; The Boeing 2460.
Requests@faa.gov.
(2) Before using any approved AMOC, Company Airplanes Examining the AD Docket
notify your appropriate principal inspector,
or lacking a principal inspector, the manager AGENCY: Federal Aviation You may examine the AD docket on
of the local flight standards district office/ Administration (FAA), DOT. the Internet at http://
certificate holding district office. ACTION: Notice of proposed rulemaking www.regulations.gov by searching for
(3) For service information that contains and locating Docket No. FAA–2015–
srobinson on DSK5SPTVN1PROD with PROPOSALS
(NPRM).
steps that are labeled as Required for 2460; or in person at the Docket
Compliance (RC), the provisions of SUMMARY: We propose to supersede Management Facility between 9 a.m.
paragraphs (h)(3)(i) and (h)(3)(ii) apply. Airworthiness Directive (AD) 2010–26– and 5 p.m., Monday through Friday,
(i) The steps labeled as RC, including
substeps under an RC step and any figures
10, which applies to certain The Boeing except Federal holidays. The AD docket
identified in an RC step, must be done to Company Model 747–200C, –200F, contains this proposed AD, the
comply with the AD. An AMOC is required –400, –400D, and –400F series regulatory evaluation, any comments
for any deviations to RC steps, including airplanes. AD 2010–26–10 currently received, and other information. The
substeps and identified figures. requires repetitive inspections for street address for the Docket Office
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Designation Authorization (ODA) whom modified before WFD develops in would substantiate and clearly warrant
we have authorized to make those airplanes. Standard inspection such an extension.
findings. techniques cannot be relied on to detect
Costs of Compliance
Explanation of Compliance Time WFD before it becomes a hazard to
flight. We will not grant any extensions We estimate that this proposed AD
The compliance time for the of the compliance time to complete any
modification specified in this proposed affects 120 airplanes of U.S. registry.
AD-mandated service bulletin related to
AD for addressing WFD was established We estimate the following costs to
WFD without extensive new data that
to ensure that discrepant structure is comply with this proposed AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Pre–modification inspections Up to 675 work-hours, = up to $0 Up to $57,375 per inspection Up to $6,885,000 per inspec-
[retained action from AD $57,375. cycle. tion cycle.
2010–26–10, Amendment
39–16549 (75 FR 81427,
December 28, 2010)].
Modification [retained action Up to 5,819 work-hours × $85 0 Up to $494,615 ...................... Up to $59,353,800.
from AD 2010–26–10, per hour = up to $494,615.
Amendment 39–16549 (75
FR 81427, December 28,
2010)].
New proposed post-modifica- Up to 105 work-hours × $85 0 Up to $8,925 per inspection Up to $1,071,000 per inspec-
tion inspections. per hour = up to $8,925. cycle. tion cycle.
We have received no definitive data For the reasons discussed above, I (a) Comments Due Date
that would enable us to provide a cost certify that the proposed regulation: The FAA must receive comments on this
estimate for the on-condition actions (1) Is not a ‘‘significant regulatory AD action by August 24, 2015.
specified in this proposed AD. action’’ under Executive Order 12866,
(b) Affected ADs
(2) Is not a ‘‘significant rule’’ under
Authority for This Rulemaking the DOT Regulatory Policies and This AD replaces AD 2010–26–10,
Procedures (44 FR 11034, February 26, Amendment 39–16549 (75 FR 81427,
Title 49 of the United States Code December 28, 2010).
specifies the FAA’s authority to issue 1979),
(3) Will not affect intrastate aviation (c) Applicability
rules on aviation safety. Subtitle I,
in Alaska, and This AD applies to The Boeing Company
Section 106, describes the authority of (4) Will not have a significant Model 747–200C, –200F, –400, –400D, and
the FAA Administrator. Subtitle VII, economic impact, positive or negative, –400F series airplanes; certificated in any
Aviation Programs, describes in more on a substantial number of small entities category; as identified in Boeing Alert
detail the scope of the Agency’s under the criteria of the Regulatory Service Bulletin 747–53A2499, Revision 3,
authority. Flexibility Act. dated July 15, 2014.
We are issuing this rulemaking under (d) Subject
the authority described in Subtitle VII, List of Subjects in 14 CFR Part 39
Air Transport Association (ATA) of
Part A, Subpart III, Section 44701, Air transportation, Aircraft, Aviation America Code 53, Fuselage.
‘‘General requirements.’’ Under that safety, Incorporation by reference,
section, Congress charges the FAA with Safety. (e) Unsafe Condition
promoting safe flight of civil aircraft in This AD was prompted by an evaluation by
The Proposed Amendment the design approval holder (DAH) indicating
air commerce by prescribing regulations
for practices, methods, and procedures Accordingly, under the authority that certain lap joints are subject to
delegated to me by the Administrator, widespread fatigue damage (WFD). We are
the Administrator finds necessary for issuing this AD to detect and correct fatigue
safety in air commerce. This regulation the FAA proposes to amend 14 CFR part
39 as follows: cracking in certain lap joints, which could
is within the scope of that authority result in rapid depressurization and
because it addresses an unsafe condition consequent reduced structural integrity of the
PART 39—AIRWORTHINESS
that is likely to exist or develop on airplane.
DIRECTIVES
products identified in this rulemaking (f) Compliance
action. ■ 1. The authority citation for part 39 Comply with this AD within the
Regulatory Findings continues to read as follows: compliance times specified, unless already
Authority: 49 U.S.C. 106(g), 40113, 44701. done.
We have determined that this
§ 39.13 [Amended] (g) Repetitive Lap Joint Inspections
proposed AD would not have federalism
srobinson on DSK5SPTVN1PROD with PROPOSALS
implications under Executive Order ■ 2. The FAA amends § 39.13 by At the applicable time specified in Table
13132. This proposed AD would not removing Airworthiness Directive (AD) 1 and Table 3 of paragraph 1.E.,
2010–26–10, Amendment 39–16549 (75 ‘‘Compliance,’’ of Boeing Alert Service
have a substantial direct effect on the
Bulletin 747–53A2499, Revision 3, dated July
States, on the relationship between the FR 81427, December 28, 2010), and 15, 2014, except as required by paragraph
national Government and the States, or adding the following new AD: (j)(1) of this AD: Do eddy current inspections
on the distribution of power and The Boeing Company: Docket No. FAA– for cracks in the skin of the lap joints, and
responsibilities among the various 2015–2460; Directorate Identifier 2014– do all applicable repairs, in accordance with
levels of government. NM–163–AD. the Accomplishment Instructions of Boeing
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![Federal Register / Vol. 80, No. 131 / Thursday, July 9, 2015 / Proposed Rules 39397
Alert Service Bulletin 747–53A2499, Bulletin 747–53A2499, Revision 3, dated July Engineer, Airframe Branch, ANM–120S,
Revision 3, dated July 15, 2014, except as 15, 2014: Internal detailed and surface HFEC FAA, Seattle Aircraft Certification Office,
required by paragraph (j)(2) of this AD. Do all inspections for any crack in the skin or 1601 Lind Avenue SW., Renton, WA 98057–
applicable repairs before further flight. internal doubler. 3356; phone: 425–917–6428; fax: 425–917–
Repeat the applicable inspections thereafter 6590; email: nathan.p.weigand@faa.gov.
(j) Exceptions to Service Bulletin Procedures
at intervals not to exceed those specified in (2) For service information identified in
Table 1 and Table 3 of paragraph 1.E., (1) Where Boeing Alert Service Bulletin this AD, contact Boeing Commercial
‘‘Compliance,’’ of Boeing Alert Service 747–53A2499, Revision 3, dated July 15, Airplanes, Attention: Data & Services
Bulletin 747–53A2499, Revision 3, dated July 2014, specifies a compliance time ‘‘after the Management, P.O. Box 3707, MC 2H–65,
15, 2014 Revision 3 date of this service bulletin,’’ this Seattle, WA 98124–2207; telephone 206–
AD requires compliance within the specified 544–5000, extension 1; fax 206–766–5680;
(h) Lap Joint Modification compliance time after the effective date of Internet https://www.myboeingfleet.com. You
At the applicable time specified in Tables this AD. may view this referenced service information
2, 4, 5, and 6 of paragraph 1.E., (2) Where Boeing Alert Service Bulletin at the FAA, Transport Airplane Directorate,
‘‘Compliance,’’ of Boeing Alert Service 747–53A2499, Revision 3, dated July 15, 1601 Lind Avenue SW., Renton, Washington.
Bulletin 747–53A2499, Revision 3, dated July 2014, specifies to contact Boeing for repair For information on the availability of this
15, 2014, except as required by paragraph instructions: Before further flight, repair material at the FAA, call 425–227–1221.
(j)(1) of this AD: Modify the applicable lap using a method approved in accordance with
the procedures specified in paragraph (l) of Issued in Renton, Washington, on June 29,
joints, in accordance with the
this AD. 2015.
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2499, Revision 3, Jeffrey E. Duven,
(k) Credit for Previous Actions
dated July 15, 2014, except as required by Manager, Transport Airplane Directorate,
paragraph (j)(2) of this AD. Accomplishment Actions done before the effective date of Aircraft Certification Service.
of the modification required by this this AD using the service information
[FR Doc. 2015–16763 Filed 7–8–15; 8:45 am]
paragraph terminates the repetitive identified in paragraph (k)(1) or (k)(2) of this
inspections required by paragraph (g) of this AD are acceptable for compliance with the BILLING CODE 4910–13–P
AD for the length of the modified lap joint. corresponding requirements of paragraphs (g)
and (h) of this AD.
(i) Lap Joint Post-Modification Inspections (1) Boeing Alert Service Bulletin 747–
53A2499, Revision 1, dated October 30, 2008,
DEPARTMENT OF THE TREASURY
At the applicable time specified in Tables
7, 8, 9, and 10 of paragraph 1.E., which is not incorporated by reference in this
AD.
Internal Revenue Service
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2499, Revision 3, dated July (2) Boeing Alert Service Bulletin 747–
53A2499, Revision 2, dated August 12, 2010, 26 CFR Parts 1, 301, and 602
15, 2014, except as required by paragraph
(j)(1) of this AD: Do the applicable which was incorporated by reference in AD
2010–26–10, Amendment 39–16549 (75 FR [REG–103281–11]
inspections specified in paragraph (i)(1),
(i)(2), or (i)(3) of this AD, in accordance with 81427, December 28, 2010).
RIN 1545–BK06
the Accomplishment Instructions of Boeing (l) Alternative Methods of Compliance
Alert Service Bulletin 747–53A2499, (AMOCs) Tax on Certain Foreign Procurement;
Revision 3, dated July 15, 2014. Repeat the Correction
(1) The Manager, Seattle Aircraft
applicable inspections thereafter at the
Certification Office (ACO), FAA, has the
applicable times specified in Tables 7, 8, 9,
authority to approve AMOCs for this AD, if
AGENCY: Internal Revenue Service (IRS),
and 10 of paragraph 1.E, ‘‘Compliance,’’ of requested using the procedures found in 14 Treasury.
Boeing Alert Service Bulletin 747–53A2499, CFR 39.19. In accordance with 14 CFR 39.19, ACTION: Correction to notice of proposed
Revision 3, dated July 15, 2014. If any crack send your request to your principal inspector
is found during any inspection, repair before
rulemaking.
or local Flight Standards District Office, as
further flight using a method approved in appropriate. If sending information directly SUMMARY: This document contains
accordance with the procedures specified in to the manager of the ACO, send it to the
paragraph (l) of this AD.
corrections to a notice of proposed
attention of the person identified in rulemaking (REG–103281–11) that was
(1) For airplanes identified as Groups 2 paragraph (m)(1) of this AD. Information may
through 5 and 8 through 10 in Boeing Alert published in the Federal Register on
be emailed to: 9-ANM-Seattle-ACO-AMOC-
Service Bulletin 747–53A2499, Revision 3, Requests@faa.gov.
Wednesday, April 22, 2015 (80 FR
dated July 15, 2014: Internal detailed and (2) Before using any approved AMOC, 22449), the proposed regulations are
surface high frequency eddy current (HFEC) notify your appropriate principal inspector, relating to the 2 percent tax on
inspections for any crack in the skin or or lacking a principal inspector, the manager payments made by the U.S. government
internal doubler. of the local flight standards district office/ to foreign persons pursuant to certain
(2) For airplanes identified as Groups 6, 11, certificate holding district office. contracts.
and 19 in Boeing Alert Service Bulletin 747– (3) An AMOC that provides an acceptable
53A2499, Revision 3, dated July 15, 2014: level of safety may be used for any repair DATES: Written or electronic comments
External detailed and low frequency eddy required by this AD if it is approved by the and request for a public hearing for the
current inspections of the upper and lower Boeing Commercial Airplanes Organization notice of proposed rulemaking at 80 FR
skin panels for cracking, external detailed Designation Authorization (ODA) that has 22449, April 22, 2015, are still being
and HFEC inspections of the doubler for been authorized by the Manager, Seattle accepted and must be received by July
cracking, and internal detailed and HFEC ACO, to make those findings. For a repair
inspections of the upper and lower skin
21, 2015.
method to be approved, the repair must meet
panels for cracking (for airplanes with a the certification basis of the airplane, and the FOR FURTHER INFORMATION CONTACT: Kate
stringer 6 lap joint modification installed approval must specifically refer to this AD. Hwa, at (202) 317–6934 (not a toll-free
srobinson on DSK5SPTVN1PROD with PROPOSALS
between STA 340 and STA 400 as specified (4) AMOCs approved for AD 2010–26–10, number).
in Boeing Service Bulletin 747–53–2272); or Amendment 39–16549 (75 FR 81427, SUPPLEMENTARY INFORMATION:
internal detailed and surface HFEC December 28, 2010), are approved as AMOCs
inspections for any crack in the skin or for the corresponding provisions of Background
internal doubler (for airplanes with lap joints paragraphs (g) and (h) this AD.
modified as specified in Boeing Alert Service The notice of proposed rulemaking
Bulletin 747–53A2499.) (m) Related Information that is the subject of this document is
(3) For airplanes identified as Groups 1, 7, (1) For more information about this AD, under section 5000C of the Internal
and 12 through 18 in Boeing Alert Service contact Nathan Weigand, Aerospace Revenue Code.
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Document Created: 2018-02-23 09:14:12
Document Modified: 2018-02-23 09:14:12
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by August 24, 2015. | |
| Contact | Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 80 FR 39394 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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