81 FR 49572 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 145 (July 28, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 145 (July 28, 2016)
| Page Range | 49572-49575 | |
| FR Document | 2016-17718 |
[Federal Register Volume 81, Number 145 (Thursday, July 28, 2016)] [Proposed Rules] [Pages 49572-49575] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-17718] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-8181; Directorate Identifier 2016-NM-002-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 adopt a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 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 proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the nose wheel well is subject to widespread fatigue damage (WFD). This proposed AD would require modification of the nose wheel body structure; a detailed inspection of the nose wheel body structure for any cracking; a surface high frequency eddy current inspection (HFEC) or an open hole HFEC inspection of the vertical beam outer chord and web for any cracking; and all applicable related investigative actions including repetitive inspections, and other specified and corrective actions. We are proposing this AD to detect and correct fatigue cracking in the nose wheel well structure; such cracking could adversely affect the structural integrity of the airplane. DATES: We must receive comments on this proposed AD by September 12, 2016. 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 NPRM, 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-2016-8181. 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. 2016-8181; 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, [[Page 49573]] any comments received, and other information. The street address for the Docket Office (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 (ACO), 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 proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. 2016-8181; Directorate Identifier 2016-NM-002-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 Fatigue damage can occur locally, in small areas or structural design details, or globally, in widespread areas. Multiple-site damage is widespread damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Widespread 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. This condition is known as widespread fatigue damage. It is associated with general degradation of large areas of structure with similar structural details and stress levels. 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. We received an evaluation by the DAH indicating that the nose wheel well is subject to WFD. This condition, if not corrected, could result in cracking in the nose wheel well structure; such cracking could adversely affect the structural integrity of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 747-53A2887, dated December 2, 2015. The service information describes procedures for modification of the nose wheel body structure; a detailed inspection of the nose wheel body structure for any cracking; a web surface HFEC and an open hole HFEC inspection of the vertical beam outer chord for any cracking; and repair. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. 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 This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ``Differences Between this Proposed AD and the Service Information.'' Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 747-53A2887, dated December 2, 2015, specifies to contact the manufacturer for certain instructions, but this AD requires accomplishment of repair methods, modification deviations, and alteration deviations 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 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 107 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: [[Page 49574]] Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Modification................. 408 work-hours x $85 $15,743 $50,423............. $5,395,261. per hour = $34,680. Part 2 detailed inspection... 140 work-hours x $85 0 $11,900 per $1,273,300 per per hour = $11,900 inspection cycle. inspection cycle. per inspection cycle. Surface HFEC inspection...... 4 work[dash]hours x 0 $340 per inspection Up to $36,380 per $85 per hour = $340 cycle. inspection cycle. per inspection cycle. Open hole HFEC inspection.... 4 work-hours x $85 0 $340 per inspection Up to $36,380 per per hour = $340 per cycle. inspection cycle. inspection cycle. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates 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 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 this 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 adding the following new airworthiness directive (AD): The Boeing Company: Docket No. 2016-8181; Directorate Identifier 2016-NM-002-AD. (a) Comments Due Date We must receive comments by September 12, 2016. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 747-100, 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, identified in Boeing Alert Service Bulletin 747- 53A2887, dated December 2, 2015. (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 indicating that the nose wheel well is subject to widespread fatigue damage. We are issuing this AD to detect and correct fatigue cracking in the nose wheel well structure; such cracking could adversely affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Modification for Groups 1 and 4 Airplanes For groups 1 and 4 airplanes as identified in Boeing Alert Service Bulletin 747-53A2887, dated December 2, 2015: Except as required by paragraph (j)(1) of this AD, at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2887, dated December 2, 2015, modify the nose wheel body structure, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2887, dated December 2, 2015. (h) Inspection for Groups 1 and 4 Airplanes For groups 1 and 4 airplanes on which the actions of paragraph (g) have been done: Except as required by paragraph (j)(1) of this AD, at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2887, dated December 2, 2015, do a detailed inspection of the nose wheel body structure for any cracking; do a surface high frequency eddy current inspection (HFEC) or an open hole HFEC inspection of the vertical beam outer chord and web for any cracking; and do all applicable related investigative, other specified actions, and corrective actions, in accordance with the Accomplishment Instruction of Boeing Alert Service Bulletin 747-53A2887, dated December 2, 2015; except as required by paragraph (j)(2) of this AD. Do all applicable related investigative actions, other specified actions, and corrective actions before further flight. Repeat the detailed inspection of the nose wheel body structure, and either the surface HFEC or the open hole HFEC inspection of the vertical beam outer chord, thereafter, at the applicable interval specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2887, dated December 2, 2015. (i) Inspection for Groups 2, 3, 5 and 6 Airplanes For groups 2, 3, 5 and 6 airplanes identified in Boeing Alert Service Bulletin 747-53A2887, dated December 2, 2015: Except as required by paragraph (j)(1) of this AD, at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2887, dated December 2, 2015, do a detailed inspection [[Page 49575]] of the nose wheel well body structure for any cracking, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2887, dated December 2, 2015; except as required by paragraph (j)(2) of this AD. Do all related investigative and corrective actions before further flight. Repeat the detailed inspection thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2887, dated December 2, 2015. (j) Exceptions to the Service Information (1) Where Boeing Alert Service Bulletin 747-53A2887, dated December 2, 2015, 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) If any crack is found during any inspection required by this AD, and Boeing Alert Service Bulletin 747-53A2887, dated December 2, 2015, specifies to contact Boeing for appropriate action, and specifies that action as ``RC'' (Required for Compliance): Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (k) 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 (l)(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, modification, or alteration 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. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) Except as required by paragraph (j)(2) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (k)(4)(i) and (k)(4)(ii) of this AD apply. (i) 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. (ii) 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. (l) Related Information (1) For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 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, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on July 21, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-17718 Filed 7-27-16; 8:45 am] BILLING CODE 4910-13-P
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taken by counsel and what disciplinary complaint. The appropriate indicating that the nose wheel well is
representations counsel did or did not disciplinary authorities are as follows: subject to widespread fatigue damage
make to the applicant in this regard. If (1) With respect to attorneys in the (WFD). This proposed AD would
the applicant submits a written United States: The licensing authority of require modification of the nose wheel
statement not executed under the a State, possession, territory, or body structure; a detailed inspection of
penalty of perjury, the Board or the Commonwealth of the United States, or the nose wheel body structure for any
immigration judge may, in an exercise of the District of Columbia that has cracking; a surface high frequency eddy
of discretion committed exclusively to licensed the attorney to practice law. current inspection (HFEC) or an open
the agency, excuse the requirement that (2) With respect to accredited hole HFEC inspection of the vertical
the written statement must be executed representatives: The EOIR disciplinary beam outer chord and web for any
under the penalty of perjury, if there are counsel pursuant to § 1003.104(a). cracking; and all applicable related
compelling reasons why the written (3) With respect to a person whom the investigative actions including
statement was not executed under the applicant reasonably but erroneously repetitive inspections, and other
penalty of perjury, and the applicant believed to be an attorney or an specified and corrective actions. We are
submits other evidence establishing that accredited representative and who was proposing this AD to detect and correct
he or she was subject to ineffective retained to represent him or her in fatigue cracking in the nose wheel well
assistance of counsel and suffered proceedings before the immigration structure; such cracking could adversely
prejudice as a result. In addition, in all courts and the Board: The appropriate affect the structural integrity of the
cases, the applicant must either submit Federal, State or local law enforcement airplane.
a copy of any applicable representation agency with authority over matters DATES: We must receive comments on
agreement in support of the affidavit or relating to the unauthorized practice of this proposed AD by September 12,
written statement or explain its absence law or immigration-related fraud. 2016.
in the affidavit or written statement. (D) The term ‘‘counsel,’’ as used in
Failure to provide any applicable this paragraph (a)(5)(iii), only applies to ADDRESSES: You may send comments,
representation agreement in support of the conduct of an attorney or an using the procedures found in 14 CFR
the affidavit or written statement may be accredited representative as defined in 11.43 and 11.45, by any of the following
excused, in an exercise of discretion part 1292 of this chapter, or a person methods:
committed exclusively to the agency, if whom the applicant reasonably but • Federal eRulemaking Portal: Go to
the applicant establishes that there are erroneously believed to be an attorney http://www.regulations.gov. Follow the
compelling reasons that he or she was or an accredited representative and who instructions for submitting comments.
unable to provide any representation • Fax: 202–493–2251.
was retained to represent him or her in
agreement. • Mail: U.S. Department of
proceedings before the immigration
(B) The applicant provides evidence Transportation, Docket Operations, M–
courts and the Board.
that he or she informed counsel whose 30, West Building Ground Floor, Room
representation is claimed to have been * * * * * W12–140, 1200 New Jersey Avenue SE.,
ineffective of the allegations leveled Dated: July 19, 2016. Washington, DC 20590.
against him or her. The applicant must Loretta Lynch, • Hand Delivery: Deliver to Mail
provide evidence of the date and Attorney General. address above between 9 a.m. and 5
manner in which he or she provided [FR Doc. 2016–17540 Filed 7–27–16; 8:45 am]
p.m., Monday through Friday, except
notice to his or her prior counsel; and Federal holidays.
BILLING CODE 4410–30–P
include a copy of the correspondence For service information identified in
sent to the prior counsel and the this NPRM, contact Boeing Commercial
response from the prior counsel, if any, Airplanes, Attention: Data & Services
or state that no such response was DEPARTMENT OF TRANSPORTATION Management, P.O. Box 3707, MC 2H–65,
received. Failure to provide the required Seattle, WA 98124–2207; telephone
Federal Aviation Administration
notice to counsel may be excused, in an 206–544–5000, extension 1; fax 206–
exercise of discretion committed 766–5680; Internet https://
14 CFR Part 39
exclusively to the agency, if the www.myboeingfleet.com. You may view
applicant establishes that there are [Docket No. FAA–2016–8181; Directorate this referenced service information at
compelling reasons why he or she was Identifier 2016–NM–002–AD] the FAA, Transport Airplane
unable to notify counsel. Directorate, 1601 Lind Avenue SW.,
RIN 2120–AA64
(C) The applicant files and provides a Renton, WA. For information on the
copy of the complaint filed with the Airworthiness Directives; The Boeing availability of this material at the FAA,
appropriate disciplinary authorities Company Airplanes call 425–227–1221. It is also available
with respect to any violation of on the Internet at http://
counsel’s ethical or legal AGENCY: Federal Aviation www.regulations.gov by searching for
responsibilities, and any Administration (FAA), DOT. and locating Docket No. FAA–2016–
correspondence from such authorities. ACTION: Notice of proposed rulemaking 8181.
Failure to provide the complaint may be (NPRM).
excused, in an exercise of discretion Examining the AD Docket
committed exclusively to the agency, if SUMMARY: We propose to adopt a new You may examine the AD docket on
the applicant establishes that there were airworthiness directive (AD) for certain the Internet at http://
Lhorne on DSK30JT082PROD with PROPOSALS
compelling reasons why he or she was The Boeing Company Model 747–100, www.regulations.gov by searching for
unable to notify the appropriate 747–100B, 747–100B SUD, 747–200B, and locating Docket No. 2016–8181; or
disciplinary authorities. The fact that 747–200C, 747–200F, 747–300, 747– in person at the Docket Management
counsel has already been disciplined, 400, 747–400D, 747–400F, 747SR, and Facility between 9 a.m. and 5 p.m.,
suspended from the practice of law, or 747SP series airplanes. This proposed Monday through Friday, except Federal
disbarred does not, on its own, excuse AD was prompted by an evaluation by holidays. The AD docket contains this
the applicant from filing the required the design approval holder (DAH) proposed AD, the regulatory evaluation,
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ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Modification ............................ 408 work-hours × $85 per $15,743 $50,423 .................................. $5,395,261.
hour = $34,680.
Part 2 detailed inspection ...... 140 work-hours × $85 per 0 $11,900 per inspection cycle $1,273,300 per inspection
hour = $11,900 per inspec- cycle.
tion cycle.
Surface HFEC inspection ....... 4 work-hours × $85 per hour 0 $340 per inspection cycle ...... Up to $36,380 per inspection
= $340 per inspection cycle. cycle.
Open hole HFEC inspection .. 4 work-hours × $85 per hour 0 $340 per inspection cycle ...... Up to $36,380 per inspection
= $340 per inspection cycle. cycle.
We have received no definitive data under the criteria of the Regulatory (f) Compliance
that would enable us to provide cost Flexibility Act. Comply with this AD within the
estimates for the on-condition actions compliance times specified, unless already
List of Subjects in 14 CFR Part 39 done.
specified in this proposed AD.
Air transportation, Aircraft, Aviation
Authority for This Rulemaking (g) Modification for Groups 1 and 4
safety, Incorporation by reference, Airplanes
Title 49 of the United States Code Safety.
For groups 1 and 4 airplanes as identified
specifies the FAA’s authority to issue The Proposed Amendment in Boeing Alert Service Bulletin 747–
rules on aviation safety. Subtitle I, 53A2887, dated December 2, 2015: Except as
section 106, describes the authority of Accordingly, under the authority
required by paragraph (j)(1) of this AD, at the
the FAA Administrator. Subtitle VII: delegated to me by the Administrator, applicable time specified in paragraph 1.E.,
Aviation Programs, describes in more the FAA proposes to amend 14 CFR part ‘‘Compliance,’’ of Boeing Alert Service
detail the scope of the Agency’s 39 as follows: Bulletin 747–53A2887, dated December 2,
authority. 2015, modify the nose wheel body structure,
PART 39—AIRWORTHINESS in accordance with the Accomplishment
We are issuing this rulemaking under DIRECTIVES Instructions of Boeing Alert Service Bulletin
the authority described in Subtitle VII, 747–53A2887, dated December 2, 2015.
Part A, Subpart III, Section 44701: ■ 1. The authority citation for part 39
‘‘General requirements.’’ Under that continues to read as follows: (h) Inspection for Groups 1 and 4 Airplanes
section, Congress charges the FAA with Authority: 49 U.S.C. 106(g), 40113, 44701. For groups 1 and 4 airplanes on which the
promoting safe flight of civil aircraft in actions of paragraph (g) have been done:
air commerce by prescribing regulations § 39.13 [Amended] Except as required by paragraph (j)(1) of this
for practices, methods, and procedures ■ 2. The FAA amends § 39.13 by adding AD, at the applicable time specified in
the Administrator finds necessary for paragraph 1.E., ‘‘Compliance,’’ of Boeing
the following new airworthiness Alert Service Bulletin 747–53A2887, dated
safety in air commerce. This regulation directive (AD): December 2, 2015, do a detailed inspection
is within the scope of that authority The Boeing Company: Docket No. 2016– of the nose wheel body structure for any
because it addresses an unsafe condition 8181; Directorate Identifier 2016–NM– cracking; do a surface high frequency eddy
that is likely to exist or develop on 002–AD. current inspection (HFEC) or an open hole
products identified in this rulemaking HFEC inspection of the vertical beam outer
(a) Comments Due Date chord and web for any cracking; and do all
action.
We must receive comments by September applicable related investigative, other
Regulatory Findings 12, 2016. specified actions, and corrective actions, in
We determined that this proposed AD (b) Affected ADs accordance with the Accomplishment
would not have federalism implications Instruction of Boeing Alert Service Bulletin
None. 747–53A2887, dated December 2, 2015;
under Executive Order 13132. This except as required by paragraph (j)(2) of this
proposed AD would not have a (c) Applicability
AD. Do all applicable related investigative
substantial direct effect on the States, on This AD applies to The Boeing Company
actions, other specified actions, and
the relationship between the national Model 747–100, 747–100B, 747–100B SUD,
corrective actions before further flight.
747–200B, 747–200C, 747–200F, 747–300,
Government and the States, or on the 747–400, 747–400D, 747–400F, 747SR, and
Repeat the detailed inspection of the nose
distribution of power and wheel body structure, and either the surface
747SP series airplanes, certificated in any
responsibilities among the various category, identified in Boeing Alert Service HFEC or the open hole HFEC inspection of
levels of government. Bulletin 747–53A2887, dated December 2, the vertical beam outer chord, thereafter, at
2015. the applicable interval specified in paragraph
For the reasons discussed above, I
1.E., ‘‘Compliance,’’ of Boeing Alert Service
certify this proposed regulation: (d) Subject Bulletin 747–53A2887, dated December 2,
(1) Is not a ‘‘significant regulatory 2015.
Air Transport Association (ATA) of
action’’ under Executive Order 12866, America Code 53, Fuselage.
(2) Is not a ‘‘significant rule’’ under (i) Inspection for Groups 2, 3, 5 and 6
(e) Unsafe Condition Airplanes
the DOT Regulatory Policies and
Lhorne on DSK30JT082PROD with PROPOSALS
Procedures (44 FR 11034, February 26, This AD was prompted by an evaluation by For groups 2, 3, 5 and 6 airplanes
1979), the design approval holder indicating that identified in Boeing Alert Service Bulletin
the nose wheel well is subject to widespread 747–53A2887, dated December 2, 2015:
(3) Will not affect intrastate aviation Except as required by paragraph (j)(1) of this
fatigue damage. We are issuing this AD to
in Alaska, and detect and correct fatigue cracking in the AD, at the applicable time specified in
(4) Will not have a significant nose wheel well structure; such cracking paragraph 1.E., ‘‘Compliance,’’ of Boeing
economic impact, positive or negative, could adversely affect the structural integrity Alert Service Bulletin 747–53A2887, dated
on a substantial number of small entities of the airplane. December 2, 2015, do a detailed inspection
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![Federal Register / Vol. 81, No. 145 / Thursday, July 28, 2016 / Proposed Rules 49575
of the nose wheel well body structure for any (ii) Steps not labeled as RC may be of the centrifugal impeller, uncontained
cracking, and do all applicable related deviated from using accepted methods in centrifugal impeller release, damage to
investigative and corrective actions, in accordance with the operator’s maintenance the engine, and damage to the
accordance with the Accomplishment or inspection program without obtaining
Instructions of Boeing Alert Service Bulletin
helicopter.
approval of an AMOC, provided the RC steps,
747–53A2887, dated December 2, 2015; including substeps and identified figures, can DATES: We must receive comments on
except as required by paragraph (j)(2) of this still be done as specified, and the airplane this NPRM by September 26, 2016.
AD. Do all related investigative and can be put back in an airworthy condition. ADDRESSES: You may send comments by
corrective actions before further flight.
Repeat the detailed inspection thereafter at (l) Related Information any of the following methods:
the applicable intervals specified in (1) For more information about this AD, • Federal eRulemaking Portal: Go to
paragraph 1.E., ‘‘Compliance,’’ of Boeing contact Nathan Weigand, Aerospace http://www.regulations.gov. Follow the
Alert Service Bulletin 747–53A2887, dated Engineer, Airframe Branch, ANM–120S, instructions for submitting comments.
December 2, 2015. FAA, Seattle ACO, 1601 Lind Avenue SW., • Mail: Docket Management Facility,
(j) Exceptions to the Service Information Renton, WA 98057–3356; phone: 425–917– U.S. Department of Transportation, 1200
6428; fax: 425–917–6590; email: New Jersey Avenue SE., West Building
(1) Where Boeing Alert Service Bulletin Nathan.P.Weigand@faa.gov.
747–53A2887, dated December 2, 2015,
Ground Floor, Room W12–140,
(2) For service information identified in Washington, DC 20590–0001.
specifies a compliance time ‘‘after the this AD, contact Boeing Commercial
original issue date of this service bulletin,’’ • Hand Delivery: Deliver to Mail
Airplanes, Attention: Data & Services
this AD requires compliance within the address above between 9 a.m. and 5
Management, P.O. Box 3707, MC 2H–65,
specified compliance time after the effective Seattle, WA 98124–2207; telephone 206– p.m., Monday through Friday, except
date of this AD. 544–5000, extension 1; fax 206–766–5680; Federal holidays.
(2) If any crack is found during any Internet https://www.myboeingfleet.com. You • Fax: 202–493–2251.
inspection required by this AD, and Boeing may view this referenced service information For service information identified in
Alert Service Bulletin 747–53A2887, dated at the FAA, Transport Airplane Directorate, this proposed AD, contact Turbomeca
December 2, 2015, specifies to contact Boeing
1601 Lind Avenue SW., Renton, WA. For S.A., 40220 Tarnos, France; phone: 33
for appropriate action, and specifies that
information on the availability of this (0)5 59 74 40 00; fax: 33 (0)5 59 74 45
action as ‘‘RC’’ (Required for Compliance):
material at the FAA, call 425–227–1221. 15. You may view this service
Before further flight, repair using a method
approved in accordance with the procedures Issued in Renton, Washington, on July 21, information at the FAA, Engine &
specified in paragraph (k) of this AD. 2016. Propeller Directorate, 1200 District
(k) Alternative Methods of Compliance Michael Kaszycki, Avenue, Burlington, MA. For
(AMOCs) Acting Manager, Transport Airplane information on the availability of this
Directorate, Aircraft Certification Service. material at the FAA, call 781–238–7125.
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the [FR Doc. 2016–17718 Filed 7–27–16; 8:45 am] Examining the AD Docket
authority to approve AMOCs for this AD, if BILLING CODE 4910–13–P
requested using the procedures found in 14 You may examine the AD docket on
CFR 39.19. In accordance with 14 CFR 39.19, the Internet at http://
send your request to your principal inspector DEPARTMENT OF TRANSPORTATION www.regulations.gov by searching for
or local Flight Standards District Office, as and locating Docket No. FAA–2016–
appropriate. If sending information directly Federal Aviation Administration 6990; or in person at the Docket
to the manager of the ACO, send it to the Operations office between 9 a.m. and 5
attention of the person identified in p.m., Monday through Friday, except
14 CFR Part 39
paragraph (l)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOC-
Federal holidays. The AD docket
[Docket No. FAA–2016–6990; Directorate
Requests@faa.gov. Identifier 2016–NE–14–AD]
contains this proposed AD, the
(2) Before using any approved AMOC, mandatory continuing airworthiness
notify your appropriate principal inspector, RIN 2120–AA64 information (MCAI), the regulatory
or lacking a principal inspector, the manager evaluation, any comments received, and
of the local flight standards district office/ Airworthiness Directives; Turbomeca other information. The address for the
certificate holding district office. S.A. Turboshaft Engines Docket Office (phone: 800–647–5527) is
(3) An AMOC that provides an acceptable in the ADDRESSES section. Comments
level of safety may be used for any repair, AGENCY: Federal Aviation
modification, or alteration required by this Administration (FAA), DOT. will be available in the AD docket
AD if it is approved by the Boeing ACTION: Notice of proposed rulemaking
shortly after receipt.
Commercial Airplanes Organization (NPRM). FOR FURTHER INFORMATION CONTACT:
Designation Authorization (ODA) that has Philip Haberlen, Aerospace Engineer,
been authorized by the Manager, Seattle SUMMARY: We propose to adopt a new Engine Certification Office, FAA, Engine
ACO, to make those findings. To be airworthiness directive (AD) for certain & Propeller Directorate, 1200 District
approved, the repair method, modification Turbomeca S.A. Arriel 1, 1A, 1A1, 1A2, Avenue, Burlington, MA 01803; phone:
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
1B, 1B2, 1C, 1C1, 1C2, 1D, 1D1, 1E, 1E2, 781–238–7770; fax: 781–238–7199;
approval must specifically refer to this AD. 1K1, 1S, and 1S1 turboshaft engines. email: philip.haberlen@faa.gov.
(4) Except as required by paragraph (j)(2) This proposed AD was prompted by an SUPPLEMENTARY INFORMATION:
of this AD: For service information that anomaly that occurred during the
contains steps that are labeled as Required grinding operation required by Comments Invited
for Compliance (RC), the provisions of modification TU376, which increases We invite you to send any written
Lhorne on DSK30JT082PROD with PROPOSALS
paragraphs (k)(4)(i) and (k)(4)(ii) of this AD the clearance between the rear curvic relevant data, views, or arguments about
apply. coupling of the centrifugal impeller and this proposed AD. Send your comments
(i) The steps labeled as RC, including
substeps under an RC step and any figures
the fuel injection manifold. This to an address listed under the
identified in an RC step, must be done to proposed AD would require removing ADDRESSES section. Include ‘‘Docket No.
comply with the AD. An AMOC is required the centrifugal impeller and replacing FAA–2016–6990; Directorate Identifier
for any deviations to RC steps, including with a part eligible for installation. We 2016–NE–14–AD’’ at the beginning of
substeps and identified figures. are proposing this AD to prevent failure your comments. We specifically invite
VerDate Sep<11>2014 14:42 Jul 27, 2016 Jkt 238001 PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 E:\FR\FM\28JYP1.SGM 28JYP1](https://thefederalregister.org/doc/81_FR_49717/page/4.svg)
Document Created: 2016-07-28 01:47:27
Document Modified: 2016-07-28 01:47:27
| 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 September 12, 2016. | |
| Contact | Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6428; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 81 FR 49572 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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